NASA Aeronautical NASA SP-7037(154)Engineering November 1982A ContinuingBibliography with Indexes S$- National Aeronautics and Space Administration MM^P^ -^ ^ •• •"• .^ Bfc. ^ Bk I at—TaW (NASA-SP-7037 ( 1 5 4 ) ) A E R O N A U T I C A L ~N83-7s277 :NGINEERING: A CONTINUING EIBLICGFAPHY WITH I N D Z X E S , S U P P L E M E N T 154 (Na t iona l a c^ T* r\ T\ 3 11^-^ s^ r-« -» n ^3 r* •*•*. »3 ? _ _ • _ • _ •* I T ( a t iona l **m Aeronaut ics and Space Administrat ion) 143 p Unclas CSCL 0 IA 00/01 08355 ' leering Aeronautical Engi •^•i • ^& • JBi _ • •^^ Bil Engineering Aeronautical _ • •^^ •1 ^^ BB • ^^ • • ^ ngineenng ronautical Engineering Aeroi ng Aeronautical Engineering " leering Aeronautical Engi I Engineering Aeronautical Ei _ • ^*^« ••• PI ^*^ • JM • •Engineei _ • ^*^« M^^HAeronautical Engineering ^ ing Aeronautical Enginee https://ntrs.nasa.gov/search.jsp?R=19830008006 2020-03-21T05:47:40+00:00Z ACCESSION NUMBER RANGES Accession numbers cited in this Supplement fall within the following ranges. STAR (N-10000 Series) N82-28243 - N82-30281 IAA (A-10000 Series) A82-38103 - A82-41587 This bibliography was prepared by the NASA Scientific and Technical Information Facility operated for the National Aeronautics and Space Administration by PRC Government Information Systems. NASASP-7037(154) AERONAUTICAL ENGINEERING A CONTINUING BIBLIOGRAPHY WITH INDEXES (Supplement 154) A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in October 1982 in • Scientific and Technical Aerospace Reports (STAR) • International Aerospace Abstracts (IAA) Scientific and Technical Information Branch 1982 National Aeronautics and Space Administration Washington, DC This supplement is available as NTISUB/141/093 from the National Technical Information Service (NTIS), Springfield, Virginia 22161 at the price of $5.00 domestic; $10.00 foreign INTRODUCTION Under the terms of an interagency agreement with the Federal Aviation Administration this publication has been prepared by the National Aeronautics and Space Administration for the joint use of both agencies and the scientific and technical community concerned with the field of aeronautical engineering. The first issue of this bibliography was published in September 1970 and the first supplement in January 1971. This supplement to Aeronautical Engineering -- A Continuing Bibliography (NASA SP- 7037) lists 511 reports, journal articles, and other documents originally announced in October 1982 in Scientific and Technical Aerospace Reports (STAR) or in International Aerospace Abstracts (IAA). The coverage includes documents on the engineering and theoretical aspects of design, construction, evaluation, testing, operation, and performance of aircraft (including aircraft engines) and associated components, equipment, and systems. It also includes research and development in aerodynamics, aeronautics, and ground support equipment for aeronautical vehicles. Each entry in the bibliography consists of a standard bibliographic citation accompanied in most cases by an abstract. The listing of the entries is arranged in two major sections, IAA Entries and STAR Entries, in that order. The citations, and abstracts when available, are reproduced exactly as they appeared originally in IAA and STAR, including the original accession numbers from the respective announcement journals. This procedure, which saves time and money, accounts for the slight variation in citation appearances. Three indexes -- subject, personal author, and contract number - are included. An annual cumulative index will be published. AVAILABILITY OF CITED PUBLICATIONS IAA ENTRIES (A82-10000 Series) All publications abstracted in this Section are available from the Technical Information Service. American Institute of Aeronautics and Astronautics, Inc. (AIAA), as follows: Paper copies of accessions are available at $8.00 per document. Microfiche"1 of documents announced in IAA are available at the rate of $4.00 per microfiche on demand, and at the rate of $1.35 per microfiche for standing orders for all IAA microfiche. Minimum air-mail postage to foreign countries is $2.50 and all foreign orders are shipped on payment of pro-forma invoices. All inquiries and requests should be addressed to AIAA Technical Information Service. Please refer to the accession number when requesting publications. STAR ENTRIES (N82-10000 Series) One or more sources from which a document announced in STAR is available to the public is ordinarily given on the last line of the citation. The most commonly indicated sources and their acronyms or abbreviations are listed below. If the publication is available from a source other than those listed, the publisher and his address will be displayed on the availability line or in combination with the corporate source line. Avail: NTIS. Sold by the National Technical Information Service. Prices for hard copy (HC) and microfiche (MF) are indicated by a price code preceded by the letters HC or MF in the STAR citation. Current values for the price codes are given in the tables on page vii. Documents on microfiche are designated by a pound sign (#) following the accession number. The pound sign is used without regard to the source or quality of the microfiche. Initially distributed microfiche under the NTIS SRIM (Selected Research in Microfiche) is available at greatly reduced unit prices. For this service and for information concerning subscription to NASA printed reports, consult the NTIS Subscription Section, Springfield, Va. 22161. NOTE ON ORDERING DOCUMENTS: When ordering NASA publications (those followed by the * symbol), use the N accession number. NASA patent applications (only the specifications are offered) should be ordered by the US-Patent-Appl-SN number. Non-NASA publications (no asterisk) should be ordered by the AD, PB, or other report number shown on the last line of the citation, not by the N accession number. It is also advisable to cite the title and other bibliographic identification. Avail SOD (or GPO). Sold by the Superintendent of Documents, U.S. Government Printing Office, in hard copy. The current price and order number are given following the availability line. (NTIS will fill microfiche requests, at the standard $4.00 price, for those documents identified by a # symbol.) Avail: NASA Public Document Rooms. Documents so indicated may be examined at or purchased from the National Aeronautics and Space Administration, Public Document Room (Room 126), 600 Independence Ave., S.W., Washington, D.C. 20546, or public document rooms located at each of the NASA research centers, the NASA Space Technology Laboratories, and the NASA Pasadena Office at the Jet Propulsion Laboratory. (1) A microfiche is a transparent sheet of film. 105 by 148 mm in size containing as many as 60 to 98 pages of information reduced to micro images (not to exceed 26 1 reduction) Avail: DOE Depository Libraries. Organizations in U.S. cities and abroad that maintain collections of Department of Energy reports, usually in microfiche form, are listed in Energy Research Abstracts. Services available from the DOE and its depositories are described in a booklet, DOE Technical Information Center - Its Functions and Services (TID-4660), which may be p.btained without charge from the DOE Technical Information Center. Avail: Univ. Microfilms. Documents so indicated are dissertations selected from Dissertation Abstracts and are sold by University Microfilms as xerographic copy (HC) and microfilm. All requests should cite the author and the Order Number as they appear in the citation. Avail: USGS. Originals of many reports from the U.S. Geological Survey, which may contain color illustrations, or otherwise may not have the quality of illustrations preserved in the microfiche or facsimile reproduction, may be examined by the public at the libraries of the USGS field offices whose addresses are listed in this introduction. The libraries may be queried concerning the availability of specific documents and the possible utilization of local copying services, such as color reproduction. Avail: HMSO. Publications of Her Majesty's Stationery Office are sold in the U.S. by Pendragon House, Inc. (PHI), Redwood City, California. The U.S. price (including a service and mailing charge) is given, or a conversion table may be obtained from PHI. Avail: BLL (formerly NLL): British Library Lending Division, Boston Spa, Wetherby, Yorkshire, England. Photocopies available from this organization at the price shown. (If none is given, inquiry should be addressed to the BLL.) Avail: Fachinformationszentrum, Karlsruhe. Sold by the Fachmformationszentrum Energie, Physik, Mathematik GMBH, Eggenstein Leopoldshafen, Federal Republic of Germany, at the price shown in deutschmarks (DM). Avail: Issuing Activity, or Corporate Author, or no indication of availability. Inquiries as to the availability of these documents should be addressed to the organization shown in the citation as the corporate author of the document. Avail: U.S. Patent and Trademark Office. Sold by Commissioner of Patents and Trademarks, U.S. Patent and Trademark Office, at the standard price of 50 cents each, postage free. Other availabilities: If the publication is available from a source other than the above, the publisher and his address will be displayed entirely on the availability line or in combination with the corporate author line. GENERAL AVAILABILITY All publications abstracted in this bibliography are available to the public through the sources as indicated in the STAR Entries and IAA Entries sections. It is suggested that the bibliography user contact his own library or other local libraries prior to ordering any publication inasmuch as many of the documents have been widely distributed by the issuing agencies, especially NASA. A listing of public collections of NASA documents is included on the inside back cover. ADDRESSES OF ORGANIZATIONS American Institute of Aeronautics and Astronautics Technical Information Service 555 West 57th Street, 12th Floor New York, New York 10019 National Technical Information Service 5285 Port Royal Road Springfield, Virginia 22161 British Library Lending Division, Boston Spa, Wetherby, Yorkshire, England Pendragon House, Inc. 899 Broadway Avenue Redwood City, California 94063 Commissioner of Patents and Trademarks U S Patent and Trademark Office Washington, D.C. 20231 Superintendent of Documents U S. Government Printing Office Washington, D.C 20402 Department of Energy Technical Information Center P.O. Box 62 Oak Ridge, Tennessee 37830 University Microfilms A Xerox Company 300 North Zeeb Road Ann Arbor, Michigan 48106 ESA-lnformation Retrieval Service ESRIN Via Galileo Galilei 00044 Frascati (Rome) Italy University Microfilms, Ltd. Tylers Green London, England Fachmformationszentrum Energie, Physik, Mathematik GMBH 7514 Eggenstem Leopoldshafen Federal Republic of Germany U S Geological Survey 1033 General Services Administration Building Washington, D.C. 20242 Her Majesty's Stationery Office P.O Box 569, S E 1 London, England NASA Scientific and Technical Information Facility PO Box 8757 B W I Airport, Maryland 21240 National Aeronautics and Space Administration Scientific and Technical Information Branch (NST-41) Washington, D.C. 20546 U.S. Geological Survey 601 E Cedar Avenue Flagstaff, Arizona 86002 U.S. Geological Survey 345 Middlefield Road Menlo Park, Cal'fornia 94025 U S. Geological Survey Bldg 25, Denver Federal Center Denver, Colorado 80225 NTIS PRICE SCHEDULES Schedule A STANDARD PAPER COPY PRICE SCHEDULE (Effective January 1, 1982) Price Code A01 A02 A03 A04 A05 A06 Page Range Microfiche 001-025 026-050 051-075 076-100 101-125 North American Price $ 4 00 6 00 7 50 9 00 10 50 12 00 Foreign Price S 800 12 00 1500 18 00 21 00 2400 A07 A08 A09 A10 A11 126-150 151-175 176-200 201-225 226-250 13 50 15 00 16 50 18 00 19 50 2700 3000 3300 3600 39 00 A12 A13 A14 A15 A16 251-275 276-300 301-325 326-350 351-375 21 00 22 50 24 00 25 50 27 00 4200 4500 4800 51 00 5400 A17 A18 A19 A20 A21 376-400 401-425 426-450 451-475 476-500 28 50 30 00 31 50 33 00 34 50 57 00 6000 6300 66 00 6900 A22 A23 A24 A25 501-525 526-550 551-575 576-600 601-up 36 00 37 50 3900 40 50 72 00 7500 78 00 81 00 -21 A99-Wri te for quote 1/ Add$1 50 for each additional 25 page increment or portion thereof for 601 pages up 21 Add $3 00 for each additional 25 page increment or portion thereof for 601 pages and more Schedule E EXCEPTION PRICE SCHEDULE Paper Copy & Microfiche Price Code E01 E02 £03 E04 E05 North American Price $ 650 7 50 9 50 11 50 13 50 Foreign Price S 13 50 15 50 1950 23 50 27 50 E06 E07 EOS E09 E10 15 50 17 50 19 50 21 50 23 50 31 50 35 50 39 50 43 50 47 50 E11 E12 E13 E14 E15 25 50 28 50 31 50 34 50 37 50 51 50 57 50 6350 6950 75 50 £16 E17 E18 E19 E20 40 50 43 50 46 50 51 50 61 50 81 50 88 50 93 50 102 50 12350 E-99-Write for quote N01 3000' TABLE OF CONTENTS Page IAA ENTRIES (A82-10000) 481 STAR ENTRIES (N82-10000) 521 Subject Index A-1 Personal Author Index EM Contract Number Index C-1 TYPICAL CITATION AND ABSTRACT FROM STAR NASA SPONSORED DOCUMENT NASA ACCESSION NUMBER TITLE- AUTHORS- CONTRACT OR GRANT- REPORT NUMBER- • N82-10021*! Kansas Univ Center for Research. Inc . Lawrence Flight Research Lab -" ICING TUNNEL TEST OF A GLYCOL EXUDING POROUS LEADING EDGE ICE PROTECTION SYSTEM ON A GENERAL AVIATION AIRFOIL Final Report • David L Kohlman. William G Schweikhard and Alan E Albright Sep 1981^37 p refs —*~ (Grant NAG3-71) I—•- (NASA-CR-165444. KU-FRL-464-1) HC A03/MF A01 CSCL 01C Avail NTIS- Test results show that the system is very effective in preventing ice accretion (anti-ice mode) or removing ice from an airfoil Minimum glycol flow rates required for antucing are a function of velocity, liquid water content in the air. ambient temperature, and droplet size Large ice caps were removed in only a few minutes using anti-ice flow rates, with the shed time being a function of the type of ice. size of the ice cap angle of attack, and glycol flow rate Wake surveys measurements show that no significant drag penalty is associated with the installation or operation of the system tested T M •AVAILABLE ON MICROFICHE LCORPORATE SOURCE -PUBLICATION DATE -AVAILABILITY SOURCE -COSATI CODE TYPICAL CITATION AND ABSTRACT FROM IAA AIAA ACCES NUMBER AUTHOR TITLE OF PERIODICAL SION \ —*A82 11317 H Development of aircraft production engineer -«- ing discipline at IIT, Bombay>N K Naik (Indian Institute of -*- Technology, Bombay, India) Aeronautical Society of India, Journal, vol 31,Feb-Nov 1979^p 119-125 The aircraft production engineering courses offered at the Indian Institute of Technology, in Bombay, are discussed To demonstrate the value of the courses, the fundamentals of aircraft production are outlined, the discussion being Confined to airframe production The loft-template method is described, and the principal loft-template scheme used in aircraft production is shown Also described are the theory and laboratory courses offered at the MVHILMDLC UN MICROFICHE TITLE — AUTHORS AFFILIATION rjATF AERONAUTICAL ENGINEERING A Continuing Bibliography (Suppl. 154) NOVEMBER 1982 IAA ENTRIES A82-38146 Efficient optimum design of structures - Program DDDU. L-X Qian.W Zhong.Y Sui.andJ Zhang (Dalian Institute of Technology, Dalian, People's Republic of China) Computer Methods in Applied Mechanics and Engineering, vol 30, May 1982, p 209-224 12 refs An efficient optimization algorithm is developed for engineering structures sub- ject to multiple constraints This highly non-linear and implicit problem is reduced to a combination of a sequence of quasi-linear constraints and explicit problems of the statically determined structures The method is based on the Kuhn-Tucker necessary conditions for optimality associated with a simple quadratic program designed simultaneously to determine the Lag range multipliers and to delete non-active constraints A number of examples including trusses and wing struc- tures show that the method is efficient when compared with other competing techniques (Author) A82-38216 Forward-swept wings add supersonic zip. R DeMeis High Technology, vol 2, Jan-Feb 1982, p 33-40 A forward-swept wing aircraft is being built under an Air Force contract for test flying in late 1983 This design has many advantages over conventional aft-swept wing aircraft, including a naturally smoother area distribution, which lowers wave drag and allows a wider fuselage at the center of gravity and, thus, provides greater payload and fuel capacity However, since twisting of the wings caused by airflow produces extreme shearing forces, the forward-swept wing design has only recently become possible by means of structural tailoring of the wing using graphita-epoxy composite material which compensates for the unstable wing twisting under standard fighter-type flying conditions In addition, the design con- fers such a responsive, unstable configuration that computer control is necessary to augment pilot action Detailed explanations of the mam aerodynamic features of the forward-swept wing design are given N B A82-38222 # Composite use on helicopters. J Ray (United Technolo- gies, Corp , Sikorsky Aircraft Div , Stratford, CT) Astronautics and Aeronautics, vol 20, July-Aug 1982, p 60, 61 Composite material used in components of the Sikorsky S-76 helicopter are reviewed Composite fiber reinforced with Nomex and an aluminum honeycomb is employed for the horizontal stabilizer The spar is equipped with caps made of unidirectional graphite-epoxy tape co-cured with Kevlar skin material Two plies of woven Kevlar cover the caps in order to prevent galvanic corrosion The inboard section of the spar possesses a precured torque tube of woven Kevlar cloth which is bonded to an aluminum core'and provides the dominant load path for torsion and flexural shear The composite materials are responsible for a 174% reduction in the airframe/gross weight ratio and an increase of 20% in the range due to the smooth flush contour of the stabilizer and consequent drag reduction The fairings and doors of the S-76 are also made of laminated struc- tures, and sandwich panels serve for the windshield support posts, internal frames, longitudinal elements and door jamb M S K A82-38223 # Toward all-composite helicopter fuselage. L Marchinski (Boeing Vertol Co , Philadelphia, PA) Astronautics and Aeronautics, vol 20, July-Aug 1982, p 61, 62 The construction and benefits of using all-composite material for helicopter fuselages, particularly on the Boeing Vertol 234, are outlined The cabin floor of the 234 is made of four composite panels with fiber glass/Kevlar 49 face sheets and a Nomex honeycomb core Molded-edge rubber seals bonded into the floor assembly during co-curing and machined 7050 aluminum fittings at each end of the lateral, Kevlar beams under the lower side of the floor panels have con- tributed to a vibration rate of less than 0 03 g A 10% weight saving over that available with an all metal floor has been achieved, as well as greater impact resistance The success with the floor indicates that replacement of all-metal fuselages with Nomex-honeycomb structures offers a potential weight savings of 33% Further research is necessary into the effects of lightning strikes and electrical bonding M S K A82-38224 # Committing composites to the Boeing 767. R Hammer (Boeing Commercial Airplane Co , Renton, WA) Astronautics and Aeronautics, vol 20, July-Aug 1982, p 62 Applications of Kevlar/graphite composites in the Boeing 767 aircraft are re- viewed, noting the higher weight savings which were achieved than were offered by metal or fiber glass/epoxy materials Results from a NASA/Lockheed pro- gram testing the Kevlar composites in comparison with fiber glass parts proved the acceptability of using the Kevlar/graphite for 24 different aircraft components at a weight savings of over 2000 Ib It is concluded that the employment and techniques involving composite technologies are at the same stage as aluminum technology was in the 1930s M S K A82-38249 Mirage 2000 - Towards possible high series production aircraft (Mirage 2000 - Vers I'avion de serie). J Monsset and N Beauclair Air et Cosmos, vol 20, July 10, 1982, p 26-42 In French Design and performance characteristics of the Mirage 2000 aircraft are presented, noting modifications available for different combat missions The sin- gle-engmed aircraft is equipped with multiple radar systems, can be used as an interceptor at high or low altitudes, is capable of carrying air-to-ground nuclear tipped missiles, and features two 30 mm cannons Fly by wire control is standard, and, the aircraft is stable at high angles of attack with a top speed of Mach 2 2 while carrying a full load at 60,000 ft The internal fuel stores are 3800 liters, and external stores can be added to extend the total range to 1500 km By wind 1980 the Mirage 2000 had been flight tested in 1677 sorties, with tests being done on five configurations of the aircraft Details of the design process, the use of com- posites in the aircraft structure, the operational features of the missile stores, the laser guidance system, and the electronics are provided M S K A82-38281 # Aerodynamic behavior of a slender slot in a wind tunnel wall. D B Bliss (Princeton University, Princeton, NJ) AIAA Journal, vol 20, Sept 1982, p 1244-1252 8 refs Grant No AF-AFOSR-77-3337 A theoretical model for the flow through a single slot of fin|te length in a wall separating a uniform freestream and a quiescent fluid at different static pressures is constructed This problem is relevant to understanding the aerodynamic behav- ior of slots which are used in the test sections of some ventilated wall transonic wind tunnels The theoretical relationship which is obtained between the pressure differential across the slot and the flow through the slot shows both the linear and quadratic regimes observed in experiments The linear behavior arises from the acceleration of the cross flow into the slot downstream of the leading edge and from the interaction of streamwise stations along the slot, as well as from the effect of slot taper Analytical solutions are obtained for two slot planform shapes, and some other cases are solved numerically The quantitative agreement with experimental data is very encouraging (Author) A82-38283 # Improved solutions to the Falkner-Skan boundary-layer equation. C A Forbrich, Jr (USAF, Armament Laboratory, Fort Walton Beach, FL) AIAA Journal, vol 20, Sept 1982, p 1306,1307 11 refs USAF-supported research The results of a state variable approach to computationally solve the Falkner- Skan equation over a wide range of boundary-layer acceleration parameters are presented The Falkner-Skan equation is concerned with flow past an infinite wedge with a particular vertex angle, and solutions are presented which are accurate to eight places for third order differential equations Iterative procedures for improving the order of accuracy are described, and an example is provided for the case of an initial wedge angle of 0 40 x pi The method is considered acceptable for the analysis of slightly accelerating and decelerating flows en- countered in low drag and supercritical airfoils M S K A82-38405 VHF radio link for ground-air-ground communications using an integrated voice-data modulation. G Benelli (Firenze, Universita, Florence, Italy) Electronics Letters, vol 18, June 24,1982, p 555,556 Consiglio Nazionale delle Richerche Contract No 81,00,202 A possible realization of a data channel between aircraft and ground station is presented, which utilizes a combined amplitude-phase modulation Amplitude modulation is used to transmit a voice signal, while phase modulation is used for 481 A82-38422 data transmission Performance of this system is evaluated through a computer simulation (Author) A82-38422 The need for a dedicated public service helicopter de- sign. R Morrison (Airborne Law Enforcement Association, Inc, Huntmgton Beach Police Dept, Huntmgton Beach, CA) Vertifhte, vol 28, July-Aug' 1982 p 28-32 A proposal is made for NASA to undertake a program to develop a technologi- cally-advanced modular helicopter designed specifically for public service use, that is, for emergency medical services, fire fighting, wildlife management, law enforcement, etc Public service helicopters currently in use have many unattrac- tive'features, such as high noise and cost, as a result of their original designs to satisfy military requirements, and are unable to meet the varied needs of public service operators The proposed helicopter would have a high speed (200-300 knots), combined with effective night, all-weather operation, and could yield na- tional benefits of over $90 billion per year, including a greater ability to compete with foreign-made helicopters, a reduced response time in emergency situations, a greater effectiveness in law enforcement, and expanded job opportunities in the helicopter industry , N B A82-38423 JVX, what an opportunity. C C Crawford. Jr (U S Army, Aviation Research and Development Command, St Louis, MO) Vertiflite, vol 28, July-Aug 1982, p 34-39 US military officials have proposed the creation of a Joint Services Advanced Vertical Lift Aircraft Program (JVX) to design a family of advanced technology vertical lift aircraft which could perform numerous, multi-service missions and achieve initial operating capability in the early 1990s Six specific roles have been selected from the mission profiles to serve as a basis for molding requirements for a common multi-service air vehicle and the requirement for fulfilling world- wide self-deployment The six roles - combat search and rescue, long range requirements, special electronics mission, signal intelligence, Marine Corps JVX, and self-deployment - are described in detail and schematics showing each of the mission profiles are included A technical assessment group, which included representatives of the US Army Aviation Research and Development Command and NASA, reviewed possible configurations for the JVX and determined that tilt rotor configurations appear to offer the best possibility for a common multi- service design since they possess adequate hover efficiency, high-altitude and high speed capabilities as well as world-wide self-deployment Other.configura- tions studied, including lift/cruise fan configurations, conventional helicopters, and the auxiliary propulsion ABC/compound helicopter, all have serious draw- backs and are considered less attractive for the JVX N B A82-38439 # Minimal order time sharing filters for INS in-flight align- ment. I Y Bar-ltzhack (Technion - Israel Institute of Technology, Haifa, Israel) Journal of Guidance, Control, and Dynamics, vol 5, July-Aug 1982, p 396-402 19 refs Research supported by the Israel Aircraft Industries, Ltd . and Ministry of Defence Very simple reduced order filters which operate in a time sharing mode are proposed for in-flight and transfer alignment of calibrated mertial navigation sys- tems (INS) such as those in fighter aircraft The coarsely aligned INS is flown for a short duration in a straight and level flight during which two second-(or third-) order time sharing filters estimate the level misalignment After removing the estimated level misalignment angles a third-(or fourth-) order filter is switched in to estimate the azimuth misalignment as the aircraft starts to maneuver in the lateral plane A true covanance simulation is carried out, which shows that the proposed filters successfully perform the fine alignment (Author) A82-38441 # Adaptive filtering for an aircraft flying in turbulent atmo- sphere. H Okubo (Osaka Prefecture University, Sakai, Japan) • Journal of Guidance, Control, and Dynamics, vol 5, July-Aug 1982, p 410-412 5 refs On the basis of a sensitivity analysis for a simple scalar system, the deteriora- tion of the Kalman filter performance resulting from incorrect noise covanance values is examined It is found that the increase in the error covanance relative to the optimum value depends largely on the ratio of the process and the meas- urement noise covanance values This is considered important in adaptive filter- ing problems when the system includes noises with extensively variable variance, such as the dynamics of aircraft flying through patches of atmospheric turbu- lence C R *A82-38442 * # Robust Kalman filter design for active flutter suppres- sion systems. W L Garrard (Minnesota, University, Minneapolis, MN), J K Mahesh, C R Stone (Honeywell Systems and Research Center, Minneapolis, MN), and H J Dunn (NASA, Langley Research Center. Hampton, VA) Journal of Guidance, Control, and Dynamics, vol 5, July-Aug 1982, p 412-414 6 refs Contract No NAS1-15486 Additional insight is provided into the use of the Doyle-Stem (1979, 1981) technique in aeroelastic control problems by examining the application of trie method to a flutter control problem The system to be controlled consists of a full-size wind tunnel model of a wing, plus an aileron, an actuator, and an accele- rometer used to sense the motion of the wing A full-state feedback controller was designed using linear optimal control theory, and a Kalman filter was used in the feedback loop for state estimation The filter design procedure is explained along with that to improve closed-loop properties of the system The locus of the poles of the filter is examined as a scalar design parameter is varied The Doyle-Stem design procedure is shown to substantially improve the stability properties of an active flutter controller designed using the linear quadratic Gaussian control theory C D A82-38443 * # Aerodynamic characteristics of a large-scale, twin tilt- nacelle V/STOL model. M D Falarski, M R Dudley (NASA, Ames Research Center, Moffett Field, CA), W Buchmann (Grumman Aerospace Corp, Beth- page, NY), and A Pisano (U S Naval Air Systems Command, Washington, DC) (American Institute of Aeronautics and Astronautics, Aerospace Sciences Meet- ing, 19th, St Louis, MO, Jan 12-15, 1981, Paper 81-0150) Journal of Aircraft, vol 19, Aug 1982. p 627-633 6 refs A subsonic tilt-nacelle V/STOL aircraft configuration is described which is powered by two turbofan engines, mounted on a single carry-through structure that is designed to maintain the thrust axis close to the center of gravity at nacelle incidences of 5-95 deg Control during V/STOL operation, often from small ship platforms, is achieved by means of a vane assembly that is immersed in each turbofan's exhaust Wind tunnel test data have been obtained with an 11 2-m wing span model for the vertical-to-honzontal flight transition capability of the concept It is found that the aircraft can operate over a broad transition corridor, with sufficient maneuver capability about the trim points The control vane exhibited linear response characteristics over a large deflection range, with little influence from power, angle of attack or ground proximity in hover The model induced a positive ground effect in hover that increased as wheel height was approached and strake angle increased O C A82-38445 * # Influence of unsteady aerodynamics on hingeless rotor ground resonance. W Johnson (NASA, Ames Research Center, Low Speed Aircraft Research Branch, Moffett Field, CA) Journal of Aircraft, vol 19, Aug 1982, p 668-673 16 refs (Previously announced in STAR as N81-28056) A82-38446 # U.S. Marine Corps AV-8A maintenance experience. L Scott and R W Mornssey (U S Naval Air Rework Facility, Cherry Point, NC) (American Institute of Aeronautics and Astronautics and NASA Ames Research Center, V/STOL Conference, Palo Alto, CA, Dec 7-9, 1981, Paper 81-2657) Journal of Aircraft, vol 19, Aug 1982, p 694-696 The basic structure of the AV-8A employs a 2014T6 aluminum alloy, with an epoxy primer and a polyurethane paint system, which have together been shown by U S Marine Corps maintenance experience to be proof against corrosion The vectorable engine nozzles and their drive system have proven to be so strong and reliable that vectoring has been used in forward flight for air combat maneuvering Only fatigue damage to the empennage primary structure has been experienced, and this problem is being addressed by a reduction of operational time at high power, together with a rebuilding of the ventral fin with solid rivets O C A82-38447 # Estimation of the peak count of actively controlled air- craft. N J Wleyerhoff and J Garlitz (U S Department of Transportation, Office Of Air and Marine Systems, Cambridge, MA) Journal of Aircraft, vol 19, Aug 1982, p 698-700 5 refs It is suggested by an analysis of preliminary data that a regression of the peak number of actively controlled aircraft on total daily operations yields an economi- cal estimate of the peak instantaneous air count (AIC) over various air route traffic control centers (ARTCCs) It is possible to have a single general regression model for the entire continental U S , or separate models for each ARTCC In addition, peak models for terminal and en route centers appear possible, and improved estimates of peak ISC may be generated by regressing on component operations, consisting of departures, arrivals and overflights, rather than total daily operations O C A82-38461 Complete flexibility and realism in radar simulation. C Buttars (International Aeradio. Ltd , Southall. Middx , England) The Controller. vol 21, May 1982, p 22, 23 A digital air traffic radar simulator, developed for International Aeradio's air traffic control training school, achieves complete flexibility and realism in all aspects ot radar training The simulator uses a mode! flight information region to provide radar training capable of being applied anywhere in the world The sys- tem has the capability to operate up to seven studen controller displays, each allowing combined radar/procedural exercises to be run Three aircraft control units are provided, each capable of controlling 16 aircraft by keyboard input The electric data display shows full aircraft data, computer replies to keyboard in- lected demands, and aircraft reports either as a result of keyboard injection or automatically The simulator is programmed with the performance envelopes of 96 aircraft types (including indicated cruising speeds, rate of climb, descent speeds between three levels, and angles of bank), and allows only realistic flight characteristics Also programmed are international standard atmosphere, and 482 A82-38786 turn and indicated air speed data, which permit the aircraft to realistically simulate actual flying conditions N B partial cavitation An essential element of these algorithms is the computation of singular integrals and the solution of singular integral equations B J A82-38462 Future terminal area systems P A Jorgensen (Selema- Industrie Elettroniche Associate S p A , Rome. Italy) (International Federation of Air Traff/c Controllers' Associations. West European Conference, Rome, Italy, Nov 12-14, 1981) The Controller, vol 21, May 1982, p 34. 35 6 refs The development of a terminal area computer system able to interface with existing flight management systems is discussed, and this type of system is intended to provide greater fuel conservation and air space capacity, with im- proved safety during the descent phase of flights The system must be able to forecast a suitable approach routing, which will allow for a continuous descent of each aircraft, while also providing optimal distribution Utilizing such a system, a controller would concentrate on monitoring the separation between the aircraft and would only rarely need to intervene in the landing process Studies are being conducted to determine optimum approach patterns for such a system with regard to fuel conservation, safety and airspace capacity A graph of the actual measured fuel consumption found for three different patterns - the standard descent profile, the low drag/low power approach, and a low drag/delayed flaps approach - is presented N B A82-38781 Symposium on Flows with Separation, Stuttgart, West Germany, November 23-25, 1981, Reports (Symposium iiber Stromungen mit Ablosung, Stuttgart, West Germany, November 23-25, 1381, Vortrage). Symposium sponsored by the Deutsche Gesellschaft fur Luft- und Raumfahrt Cologne, Deutsche Gesellschaft fur Luft- und Raumfahrt, 1982 147 p In German and English (For individual items see A82-38782 to A82-38786) Aspects of viscous transonic airfoil flow simulation are considered along with investigations regarding vortex formation at wings with bent leading edges, lead- ing edge separation at delta wings with curved leading edges in supersonic flow, and measurement and visualization of skin friction on the leeside of delta wings in supersonic flow Attention is given to measurements of velocity distributions in the leading edge vortex of a delta wing by the laser-Doppler procedure, the topological structure of separated flows with three-dimensional boundary condi- tions, the calculation of boundary layers at fuselages, and a delta wing with a high vortex stability Other topics investigated are related to an experimental study concerning two- and three-dimensional separation, and a theoretical investigation of separated flows in cascades of fluid kinetic machines G R A82-38463 The detection of low level wind shear. II. P D Simmons The Controller, vol 21, May 1982, p 36-38 The Low Level Wind Shear Alert System (LLWSAS), a real-time micro-comput- er-controlled, data acquisition, analysis and display system for detecting horizon- tal wind shear near airports, is discussed, and the system's performance since its introduction by the FAA beinmng in 1977 is analyzed The system collects wind direction and wind speed data from six anemometers located near approach and takeoff areas of the airport, computes the wind gusts, and alerts controllers to wind shears by visual and audible alarms, and the information is then relayed to pilots in the area While proof of the effectiveness of a system of this nature is extremely difficult to establish, it is noted that there have been no wind shear accidents in the US since 1977 One incident attributed to wind shear which occurred in Atlanta in 1979, but did not result in an accident, is discussed in detail While the LLWSAS did not dectect wind shear conditions, it is shown that the wind shear occurred outside of the range of the system, but at a distance which allowed the pilot to recover and land safely N B A82-38464 Fuel conservation: The airline - ATC. P M Grundy The Controller, vol 21, May 1982, p 39, 40, 47 The air traffic control system has a greater impact on fuel conservation than any other factor in aviation, the most energy intensive industry in the world The article discusses various measures that could be adopted by airlines and air traffic controllers to increase fuel conservation These include reducing operating empty weights, flying at optimum altitude, direct routing, linear holding, speed control, flight planning, loading for favorable center of gravity to reduce trim drag, minimizing route mileage, and clearance priorities for more fuel demanding air- craft during landing N B A82-38474 A simplified approach to the free wake analysis of a hovering rotor. R H Miller (MIT, Cambridge, MA) (Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 7th, Garmisch-Partenkirchen, West Germany, Sept 8-11, 1981) Vertica, vol 6, no 2, 1982, p 89-95 19 refs (Previously announced in STAR as N82-18121) A82-38475 Calculation of the cross section properties and the shear stresses of composite rotor blades. R Worndle (Messerschmitt- Bolkow-Blohm GmbH, Munich, West Germany) (Deutsche Gesellschaft fur Luft- und Raumfahrt, European Rotorcraft and Powered Lift Aircraft Forum, 7th, Gar- misch-Partenkirchen, West Germany, Sept 8-11, 1981) Vertica, vol 6, no 2, 1982, p 111-129 10 refs (Previously announced in STAR as N82-25334) A82-38500 # Wind shear - Its effect on an aircraft and ways to reduce the hazard. II (Uskok wiatru - Dzialanie na samolot, srodki zmniejszajace zagrozenie. II). J M Morawski and T Smolicz (Instytut Lotnictwa, Warsaw, Poland) Technika Lotnicza i Astronautyczna, vol 37, May 1982, p 5-8 7 refs In Polish A82-38722 t Numerical methods for solving boundary value prob- lems for noncavitating and cavitating flow past wing profiles (Chislennye melody resheniia kraevykh zadach beskavitatsionnogo i kavitatsionnogo obtekanna kryl'evykh profilei) N lu Zavadovskn, S S Maslennikov, and A A Rusetskn (Tsentral'nyn Nauchno-lssledovatel'skn Institut, Leningrad, USSR) Gi- dromekhanika, no 45, 1982. p 3-12 6 refs In Russian Algorithms are developed for the numerical solution of the following problems of the steady flow of an ideal incompressible fluid noncavitating flow past an airfoil section, noncavitating flow past a wing profile, and flow past a profile with A82-38783 # Investigations regarding vortex formation at wings with bent leading edges (Untersuchungen iiber die Wirbelbildung an Flugeln mit geknickten Vorderkanten). U Brennenstuhl and D Hummel (Braunschweig, Technische Universitat, Brunswick, West Germany) In Symposium on Flows with Separation. Stuttgart, West Germany, November 23-25, 1981, Reports (A82- 38781 19-02) Cologne, Deutsche Gesellschaft fur Luft- und Raumfahrt, 1982 4 p In German It is pointed out that modern bomber aircraft employ presently almost exclu- sively wings with bent leading edges There is currently a shortage of wind tunnel data which can provide detailed information regarding the characteristics of flows around such wings For these reasons, an experimental program involving the study of a number of wings with the considered characteristics has been con- ducted in West Germany The first results obtained in connection with this pro- gram have already been reported by Brennenstuhl and Hummel (1981) The present investigation is concerned with the remainder of the results obtained in the investigation The effect of the angle by which the leading edge is bent on the flow characteristics is considered Attention is given to measurements concerning the pressure distribution and the flowfield G R A82-38784 # Leading edge separation at delta wings with curve---' leading edges in supersonic flow (Vorderkantenablosung an Deltafliigeln mit gekrummten Vorderkanten im Uberschall). R Henke (Berlin, Technische Universitat, Berlin, West Germany) In Symposium on Flows with separation, Stuttgart, West Germany, November 23-25, 1981, Reports (A82-38781 19-02) Cologne, Deutsche Gesellschaft fur Luft- und Raumfahrt, 1982 14 p 6 refs In German Leeside flow types for delta wings are considered, taking into account the boundary provided by the Stanbrook-Squire region which divides the separation forms 'leading edge separation' and 'shock induced separation' Basic information regarding the flow over wings with curved leading edges was obtained in studies conducted by Henke (1980) and by Ganzer and Henke (1981) An evaluation of oil film pictures provided an impression regarding the interference characteristics for the various wing components A number of graphs are presented for the illustration of the obtained results Some of the pictures were obtained by means of a vapor screen technique and a schlieren method G R A82-38785 * # Measurement and visualization of skin friction on the leeside of delta wings in supersonic flow (Messung und Sichtbarmachung der Wandschubspannungen auf der Leeseite von Deltafliigeln im Uber- schall). J Szodruch (Vereinigte Flugtechnische Werke-Fokker GmbH, Bremen, West Germany) and D J Monson (NASA, Ames Research Center, Moffett Field. CA) In Symposium on Flows with Separation, Stuttgart, West Germany, Novem- ber 23-25, 1981, Reports (A82-38781 19-02) Cologne, Deutsche Gesellschaft fur Luft- und Raumfahrt, 1982 9 p 7 refs In German The reported investigation was conducted with the aid of the NASA Ames High Reynolds Number Wind Tunnel The flow conditions considered involved free stream Mach numbers of 2 and 3, and a Reynolds number of approximately 10,000,000 p m The employed model was a delta wing with an angle of 70 deg A method reported by Tanner (1977) was used for the measurement of the skin friction This method involves the use of a laser interferometer to determine the change in the thickness of an oil film The procedure can also be employed for a visualization of skin friction in the form of mterferograms The investigation shows that skin friction measurements can provide a significant contribution to a physical understanding of the flow processes at the delta wing G R A82-38786 # Measurements of velocity distributions in the leading edge vortex of a delta wing by the laser-Doppler procedure (Messungen 483 A82-38922 von Geschwindigkeitsverteilungen im Vorderkantenwirbel eines Deltaflu- gels mit dem Laser-Doppler-Verfahren). K Anders (Institut fur Ther- modynamik der Luft- und Raumfahrt, Stuttgart, West Germany) and E Wedemeyer (Institut von Karman de Dynamique des Fluides, Rhode-Samt- Genese, Belgium) In Symposium on Flows with Separation, Stuttgart, West Germany, November 23-25. 1981, Reports (A82-38781 19-02) Cologne, Deut- sche Gesellschaft fur Luft- und Raumfahrt, 1982 11 p In German It is pointed out that there are significant differences between the flow around a.delta wing and the flow observed in the case of a conventional wing with a large aspect ratio Vortex formation at the leading edges of delta wings produces nonlinear additional lift Under certain conditions, a complete change of the form of the flowfield will occur above a part of the wing, and the vortex will burst Pronounced turbulent mixing takes place, and the supersonic speed is signifi- cantly reduced This reduction leads to a considerable decrease of the lift Lud- wieg (1960) has discussed a theory which explains the bursting process with an occurrence of instabilities The present investigation is concerned with a study of leading edge vortices on the basis of Ludwieg's theory Certain deviations of experimental data from results obtained on the basis of Ludwieg's theory can, perhaps, be explained by the unsymmetncal character of the vortex near the wall GR on-board computer for real-time missile avoidance Also presented is a, table look-up approach This approach permits maneuvering at longer ranges, appears better able to handle a multiple missile scenario as compared with an optimal control algorithms, and appears more feasible to implement .-,> C,R ' ? -^ , -» A82-38940 # Pilot models for discrete maneuvers. R K Hefffey (Sys- tems Technology, Inc . Mountain View, CA) In Guidance and Contro( Confer- ence, San Diego. CA, August 9-11, 1982. Collection of Technical' Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 132-142 17 rets (AIAA 82-1519) <*c.~ ••:•*?. Discrete maneuvers comprise a class of piloting tasks which can include fixed- wing landing flare, gross change of heading, altitude, or airspeed, helicopter or VTOL transition to hover, and helicopter nap-of-the-earth dash and quick-stop While these maneuvers may appear to differ fundamentally from basic tracking tasks, pilot models can be constructed using the same mathematical forms Several examples of discrete-maneuver pilot models are presented along >with accompanying flight and simulator data The value of such models is discussed with regard to handling qualities, simulator fidelity, and pilot training The mam benefit is the ability to exploit pilot-in-the-loop analysis more effectively by for- mulating a complete pilot-vehicle-task context (Author) A82-38922 Calculation of level flow using radial grating (Berech- nung der ebenen Stromung durch rotierende Radialgitter). E M Steck (Karl- sruhe, Umversitat, Karlsruhe, West Germany) (Gesellschaft fur angewandte Mathematik und Mechamk, Wissenschaftliche Jahrestagung, Wurzburg, West Germany, Apr 21-24, 1981) Zeitschnft fur angewandte Mathematik und Me- chamk. vol 62, Apr 1982, p T 233-T 235 In German A theoretical study of level flow through a rotating radial grating is conducted for the special case of ideal flow as well as for laminar flow in a high-viscosity newtonian fluid A system of equations and correlative boundary conditions are developed in order to obtain the frictional and friction-free flow in the form of the integral values of the pressure and efficiency as functions of volume, blade number, Reynolds number, blade angle variation, and radian ratio C D A82-38937 # A recursive terrain height correlation system using mul- tiple model estimation techniques. G L Mealy and W Tang (Analytic Sciences Corp , Reading, MA) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 105-112 -7 refs Grant No DAKK80-79-C-0268 (AIAA 82-1513) This paper describes the results of an investigation of the performance capabili- ties of an extended Kalman filter (EKF) based recursive terrain correlation system proposed for low-altitude helicopter navigation The major disadvantage of this concept is its sensitivity to initial position error One method for reducing this sensitivity involves the use of multiple model estimation techniques In the multiple model approach, a bank of identical EKFs, each of which is initialized at a different point in the a priori uncertainty basket, is employed to ensure that one filter is initialized near the true aircraft position In this manner, the probability of filter convergence is increased substantially, leading to improved navigation perform- ance ' (Author) A82-38938 # PNCS - A commercial flight management computer sys- tem. M W Bird (Lear Siegler, Inc , Instrument Div , Grand Rapids, Ml) In Guid- ance and Control Conference, San Diego, CA, August 9-11, 1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronau- tics and Astronautics, 1982, p 113-123 5 refs (AIAA 82-1515) The Performance Navigation Computer System (PNCS), a system in which performance optimization, multisensor navigation, automatic guidance, and dis- play techniques have been integrated to provide fuel-efficient operation and a lower workload for the crew is described The PNCS guidance and flight planning capabilities derive from the integration of the optimum speed and altitude profiles computed by the performance management function with the lateral path and speed/altitude constraints of the flight plan The performance management func- tions determine the climb, cruise, and descent profile segments that minimize the total trip cost, while lateral, vertical, and speed commands are fed to the autopilot and autothrottle for automatic guidance to the optimized profile The navigation data base of the PNCS, which contains airport, route, and navigation aid data, simplifies the selection and modification of flight plans C R A82-38939 # Air-to-air missile avoidance. G A Mandt and T L Neigh- bor (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB, OH) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 124-131 12 refs (AIAA 82-1516) A methodology for developing real-time missile avoidance trajectories is presented The steps are as follows analyzing missile systems for vulnerabilities, determining the tactics to exploit these vulnerabilities, and testing the tactics against missile simulations to determine the location and extent of maneuver effectiveness It is noted that these maneuvars could then be placed into an A82-38941 # Design and flight testing of digital direct side-force con- trol laws. S L Grunwald (USAF. Washington, DC) and R F Stengel (Princeton University, Princeton, NJ) In Guidance and Control Conference. San Diego'. CA. August 9-11,1982, Collection of Technical Papers (A82-38926 19-18) New fork, American Institute of Aeronautics and Astronautics, 1982. p 143-151 15 refs Contract No N00014-78-C-0257 (AIAA 82-1521) Three-input/three-output command augmentation control laws designed and tested in flight using Princeton University's variable-response research aircraft are discussed It is noted that the controllers were based on algebraic model- following, a fast and efficient method of direct digital synthesis for advanced control modes Pilot opinions of several command modes and controller-to-cdm- mand pairings are presented here Flat turns, lateral translation, and roll control are investigated Of the command modes tested, foot pedals-to yaw rate, lateral stick-to-roll rate, and thumb lever-to-sideslip angle are found to give the best overall ratings C R A82-38942 # Simulator investigations of various side-stick control- ler/stability and control augmentation systems for helicopter terrain flight. E W Aiken (U S Army, Aeromechanics Laboratory, Moffett Field, CA) In Guid- ance and Control Conference, San Diego, CA, August 9-11, 1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronau- tics and Astronautics, 1982, p 152-164 15 refs (AIAA 82-1522) Two piloted simulator experiments were conducted to assess the effects of side-stick-controller characteristics and level of stability and control augmenta- tion on handling qualities for helicopter terrain flight A composite of several evaluation tasks was flown with the aid of a head-up display of flight-control symbology Variations in force-deflection characteristics and the number of axes controlled through a side-stick were investigated Satisfactory handling qualities were achieved with a two-axis displacement controller and angular rate stabiliz'a- tion Attitude stabilization was required to maintain adequate handling qualities for either a three- or four-axis rigid controller (Author) A82-38943 * # The effects of the delays on systems subject to manual control. R A Hess (NASA, Ames Research Center, Moffett Field, CA) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 165-172 13 refs Results are presented of an experimental study to determine the effects of time delays in manual control systems A simple, fixed-base laboratory simulation facility is used for determining pilot dynamics and tracking performance in a series of single-axis, compensatory tracking tasks In these tasks, three time-delay values and three controlled-element dynamics are used The delays are chosen to encompass values encountered in experimental and operational aircraft It is noted that the controlled-element dynamics replicate those found in many previ- ous manual control studies, that is, the classical displacement, rate, and acceler- ation control systems The experimental effort is complemented with an analytical pilot modeling study where the parameters of a structural model of the human pilot are adjusted so as to provide excellent matches to the experimentally determined pilot dynamics The experimental and analytical studies both indicate that time delays cause significant changes in pilot equalization requirements CR A82-38944 * # Modal control of relaxed static stability aircraft. R H Rooney, J C Chung, and E Y Shapiro (Lockheed-California Co , Burbank, CA) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collec- tion of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 173-176 Contract No NAS1-15326 (AIAA 82-1524) 484 A82-38990 - A method is developed that assigns a selected portion of a closed loop system - eigenstructure in accordance with certain desirable critera The method is applied •'here to a relaxed static stability aircraft, the goal being to synthesize a control Haw that provides the unstable aircraft with handling qualities equal to or better than those of a comparable statically stable aircraft It is shown that by using the target system eigenstructure, good flight characteristics are achieved by the unstable [aircraft It is also shown that improved characteristics can be obtained by assigning'an orthogonal eigenvector structure C R A82-38954 # An X-Wing aircraft control system concept. A J Potthast (Lockheed-California Co , Burbank. CA) In Guidance and Control Conference, San Diego, CA, August 9-11, 1982, Collection of Technical Papers (A82-38926 >19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p .257-265 13refs (AIAA 82-1540) .X-Wing aircraft technology development has, as an ultimate goal, a Vertical "Take-Off and Landing (VTOL) aircraft with fast tactical response, long range, and 'high speed that can be operated from frigates and large destroyers The 'proposed aircraft combines a circulation control air rotor/wing and control sys- temiwith a conventional aircraft fuselage and 'fan-in-fm' tail Cyclic and collective modulation of rotor/wing circulation control air combined with rotor/wing hub moment feedback and conventional feedback provides continuous stability and control during rotary, conversion, and fixed wing modes of flight The control .concept is described and test results from full and 1 /4-scale models are com- pared with predicted data Conclusions are drawn relative to concept application to the X-wing aircraft (Author) A82-38969 # A design criterion for highly augmented fly-by-wire air- ~craft. C R Abrams (U S Navy, Air Development Center, Warminster, PA) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collection .pf Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 410-419 8 refs (AIAA 82-1570) The present investigation is concerned with a versatile control criterion for highly augmented fly-by-wire aircraft which can provide optimized mission-on- . ented performance Based on an optimization process for a second order system, a Time Response Parameter (TRP) has evolved which can be adapted to a variety of mission phases and new flight modes The TRP approach has demon- strated definite trends with both Pilot Ratings and Pilot Induced Oscillation Rat- Ings, and is also compatible with other transient response criteria The TRP 'criterion can be readily applied to high order, nonlinear, and multivanable control systems, and is easily computerized for continuous evaluation of control system '•design It is pointed out that the use of such criteria will promote the utilization of military aircraft as a weapons platform through more effective flight control de- sign G R A82-38980 # Generic faults and design solutions for flight-critical systems. S S Osder (Sperry Flight Systems, Phoenix, AZ) In Guidance and "Control Conference, San Diego, CA, August 9-11, 1982, Collection of Technical ^Papers (A82-38926 19-18) New York, American Institute of Aeronautics and "Astronautics, 1982, p 509-518 17 refs (AIAA 82-1595) f> The term 'generic fault' is employed to describe design defects which elude the i test and analysis procedures used to validate a redundant control system design 'Although the existence of such defects can be postulated in any type of system, the generic fault concept is especially significant in the flight-critical system ap- plication because it defeats the massive redundancy strategies which designers rely on to meet safety or reliability objectives Various types of generic faults are examined, taking into account computation and scaling, timing, logical errors, hardware and firmware defects, latent failure effects, and aspects of real-time clock failure A description is presented of solutions using decoupled, nonsyn- chronous architectures It is found that dissimilar redundancy and brick-wall sepa- ration strategies are viable approaches to overcome generic-fault vulnerabilities Their implementation requires unsynchronized channel operation G R A82-38981 * # The use of differential pressure feedback in an auto- matic flight control system. D W Levy, J Roskam, and P D Finn (Kansas University Center for Research, Inc , Flight Research Laboratory, Lawrence, KS) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collec- tion of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 519-524 Grant No NAG4-5 (AIAA •-82-1596) A feasibility study has been performed to evaluate the performance of a system whereby a control surface is positioned with differential pressure as the feedback variable Analogous to a position command system, the control surface is com- manded to move until a certain differential pressure is achieved at a given point on the surface Frequency response tests and theoretical considerations indicate that the pressure feedback transfer function is first order, with a break frequency up to 50 rad/sec There exist applications to the outer loops of flight control systems as well Stability augmentation, gust alleviation, and stall prevention appear to be possible by feeding back differential pressure across lifting and control surfaces (Author) A82-38982 # A preliminary laboratory evaluation of a reconfigurable integrated flight control concept. A P DeThomas (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, OH) and S C Goel (Systems Control Tech- nology, Inc . West Palm Beach, FL) In Guidance and Control Conference, San Diego, CA, August 9-11, 1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 525-530 5 refs (AIAA 82-1597) The present investigation is concerned with the concept of virtual redundancy as a means of maintaining the reliability of the flight control function within an integrated architecture Virtual redundancy involves the reconfiguring of the sys- tem resources to create redundancy on demand Virtual redundancy is invoked by the system executive by causing some known good processor to compute a solution which can break the tie between disagreeing processors An implemen- tation in software for the case of Virtual Flight Control redundancy is discussed Attention is given to an examination of virtual redundancy as a means of fault isolation for cross-channel monitoring when only two signals are present, a gen- eral assessment of the feasibility of virtual redundancy and system reconfigura- tion to enhance coverage and recover function lost due to failures, redundancy management, and failure detection and isolation G R A82-38986 # The ideal controlled element for real airplanes is not K/s. C R Chalk (Calspan Corp , Buffalo, NY) In Guidance and Control Confer- ence, San Diego, CA, August 9-11, 1982, Collection of Technical Papers (A82- 38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 556-560 (AIAA 82-1606) The early experiments performed to generate data to support development of mathematical models of the human operator used simple controlled element transfer functions, including K, and K/s However, when the physical system being controlled has mass and the response state being controlled is position, the K and K/s transfer function forms are physically impossible because infinite acceleration capability would be required for abrupt commands It is found that the roll angular acceleration and the lateral linear accelerations at the pilot station are important considerations in flying qualities The angular and linear accelera- tions can become objectionably high when the roll damping is very high and the height above the X stability axis is large It is pointed out that roll ratchet is best explained by a model that assumes the pilot is closing the aileron loop on angular acceleration response cues G R A82-38988 # An alternate method of specifying bandwidth for flying qualities. J Hodgkmson.J R Wood (McDonnell Aircraft Co , St Louis, MO), and R H Hoh (Systems Technology, Inc , Ha/rthorne, CA) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronau- tics. 1982, p 571-578 6 refs (AIAA 82-1609) It is pointed out that the task of predicting the flying qualities of a modern fighter aircraft has been complicated by the use of highly augmented control systems Control systems intended to improve flying qualities have often degraded them instead These degradations were unexpected because the criteria used to pre- dict.the aircraft's flying qualities were invalid, or were incorrectly interpreted, for augmented aircraft Therefore, in the 'Proposed MIL Standard/Handbook - Hand- ling Qualities of Piloted Airplanes', criteria for augmented aircraft are empha- sized The bandwidth criterion specifies the quality of aircraft attitude dynamics A refined version of the bandwidth criterion is proposed The new version offers two specific advantages as compared with the original version It deals with the bandwidth sensitivity problem and, by using a Nichols chart, it encourages the designer to view the entire open- and closed-loop frequency responses simul- taneously G R A82-38989 # Investigation of low order lateral directional transfer function models for augmented aircraft. D E Bischoff and R E Palmer (U S Naval Material Command, Naval Air Development Center, Warminster, PA) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 579-586 11 refs (AIAA 82-1610) The high order transfer functions representing the lateral directional responses of augmented aircraft to pilot control inputs were matched in the frequency domain with two candidate low order equivalent forms (1) the complete three degree of freedom representation of roll and sideslip angle responses, and (2) the single degree of freedom roll mode and Dutch roll approximations Accepta- ble models were generally obtained for both forms Simultaneous matching of sideslip and roll angle responses and/or a priori information for the roots was required to match the full three degree of freedom forms The equivalent system models are discussed in terms of their match statistics and their modal parame- ters are compared against the requirements of the military flying qualities specifi- cation (Author) A82-38990 " # An analysis of a nonlinear instability in the implementa- tion of a VTOL control system during hover. J M Weber (NASA, Ames Research Center, Morfett Field, CA) In Guidance and Control Conference, San Diego, CA, August 9-11, 1982, Collection of Technical Papers (A82-38926 485- A82-38995 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 587-596 7 refs (AIAA 82-1611) (Previously announced in STAR as N82-22281) A82-38995 # Target acquisition system/air-to-surface weapon com- patibility analysis. A R Mitchell (Analytic Sciences Corp, Reading, MA) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 638-642 (AIAA 82-1618) The paper presents a simple, closed form method which has been developed for compatibility analysis of an autonomous target acquisition system with an air-to-surface weapon The output is a probability distribution for expected target location at the moment of potential weapon release Compatibility is measured by the probability that the target lies in the footprint of the released weapon The method uses statistical input data on terrain masking, atmospheric obscuration, and the acquisition system timeline from first target detection through classifica- tion, designation and weapon release Generic results are presented for a hypo- thetical target acquisition system (Author) A82-38998 # The Shiryayev sequential probability ratio test for redundancy management. J L Speyer and J E White (Texas, University, Austin, TX) In Guidance and Control Conference, San Diego, CA, August 9-11, 1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 658-666 10 refs (AIAA 82-1623) An essential aspect in the design of fault tolerant digital flight control systems is the design of failure detection and redundancy management systems A deci- sion rule, the Shiryayev sequential probability ratio test (SPRT), is used to detect failures between similar instruments, as well as between dissimilar instruments through analytic redundancy Unlike the Wald SPRT, which tests for the presence of failure or no failure in all of the data sequence, the Shiryayev SPRT detects the occurrence of a fault in the data sequence in minimum time if certain condi- tions are met The performance of the Shiryayev SPRT in detecting a failure between two rate gyros as compared to standard fixed interval schemes is presented, as is the performance for a single accelerometer failure using transla- tional kinematic equations to form a parity relation for analytic redundancy (Author) A82-39003 # X-29A flight control system design experiences. J Chin, H Berman, and J Ellmwood (Grumman Aerospace Corp, Bethpage, NY) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 703-713 11 refs (AIAA 82-1538) The X-29A aircraft is a technology demonstrator consisting of a structurally tailored forward swept wing, an automatic camber control concept to increase aerodynamic efficiency, a high level of aircraft relaxed static stability (RSS), and a digital fly-by-wire flight control system using control laws designed via modern optimal control techniques A description is presented of the considerations exer- cised during the design and development of the flight control system (PCS), and attention is given to the uniqueness of the X-29A aircraft which led to high levels of RSS for minimum PCS requirements The advantages of RSS are discussed along with the longitudinal control requirements, the control modes, aspects of control law development, and questions of flight control system validation GR A82-39009 * # The effects of atmospheric turbulence on a quadrotor heavy lift airship. M B Tischler and H R Jex (Systems Technology, Inc, Hawthorne, CA) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collection of Technical Papers (A82-38926 19-18) New York, Ameri- can Institute of Aeronautics and Astronautics. 1982, p 767-776 15 refs Contract No NAS2-10330 (AIAA 82-1542) The response of a quadrotor heavy lift airship to atmospheric turbulence is evaluated using a four-point input model Results show interaction between gust inputs and the characteristic modes of the vehicle's response Example loop closures demonstrate tradeoffs between response regulation and structural loads Vehicle responses to a tuned discrete wave front compare favorably with the linear results and illustrate characteristic HLA motion (Author) A82-39011 # Analyzing stable pad disturbances and design of a sen- sor vault to monitor pad stability. O D Starkey, J D Kerr, and L D Hall (Teledyne, Inc , Teledyne Geotech, Garland, TX) In Guidance and Control Con- ference, San Diego, CA, August 9-11, 1982, Collection of Technical Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 785-788 (AIAA 82-1585) Among disturbing environmental mechanisms are tidal variations in gravity, natural and cultural seisrnic activity, and acoustic excitation of components An analysis is presented, of these disturbances Also described is the development of a vault that isolates1 the sensors from external disturbances yet provides close coupling to the test pad Initial tests carried out on a prototype vault installed in February 1982 show that a feedback-type seismometer can mc'ude a sustained oscillation within its housing A possible analysis of this phenomenon is included CR A82-39013 # Avoiding the pitfalls in automatic landing control sys- tem design. A A Lambregts (Boeing Commercial Airplane Co , Seattle. WA) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collec- tion of Technical Papers (A82-38926 19-18) New York. American Institute of Aeronautics and Astronautics, 1982, p 799-809 (AIAA 82-1599) This paper relates recent experiences at Boeing with the development and flight testing of improved automatic landing flare control laws for the B-737 and B-747 aircraft Some earlier designs and their limitations are reviewed Basic requirements for flare law initiation, command synchronization, feedback signal sources and characteristics, inner loop configurations, elevator control band width and throttle control are discussed Experiences and potential pitfalls in the development of integrated glide slope and flare control laws for improving an existing B-747-SP design and for a new B-737 SP-177 autopilot are described Analog computer design constraints are reviewed A 'variable tau' flare law con- cept, using groundspeed to reduce longitudinal dispersion and achieve a constant flare height are discussed as well as an 'explicit trajectory' flare control concept to achieve the same goals, along with flight test results New design options using digital computers are pointed out (Author) A82-39016 # Flight control synthesis using robust output observers. E G Rynaski (Calspan Advanced Technology Center. Buffalo, NY) In Guidance and Control Conference, San Diego, CA, August 9-11,1982, Collection of Techni- cal Papers (A82-38926 19-18) New York, American Institute of Aeronautics and Astronautics, 1982, p 825-831 (AIAA 82-1575) A brief investigation is made of the application of robust output observer theory to the design of flight control systems for advanced aircraft configurations Ob- server theory is seen as a natural design tool because the resulting observers are in themselves unobservable and do not increase the order of the closed-loop response, thereby more closely satisfying flying qualities requirements Exam- ples are adduced to show that the observer configuration is not unique in either the observer poles or the output sensors and that many different control system configurations using a variety of sensors can be designed to yield identical closed-loop dynamic behavior In this way, it becomes possible to incorporate considerable analytic and physical redundancy into nearly any flight control sys- tem C R A82-39081 # Handling qualities criteria for flight path control of V/STOL aircraft. M B Tischler and R H Hoh (Systems Technology, Inc, Hawthorne, CA) American Institute of Aeronautics and Astronautics, Atmo- spheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1292 10 p 14 refs Contract No N62269-80-C-0290 Tentative handling qualities criteria for V/STOL path control have been devel- oped based on a study of bandwidth requirements and lower-order equivalent system representations This work extends the equivalent system concept from smgleloop to multiloop applications Numerical results show the significant influ- ence of inter-axis coupling on maximum attainable piloted bandwidth Preliminary fixed-base simulation results verify the expected trends and correlate well with the analytically derived boundaries proposed in this paper (Author) A82-39082 * # Piloted simulator evaluation of a relaxed static stability fighter at high angle-of-attack. M Lapms, R W Klein, R P Martorella, J Cangelosi (Grumman Aerospace Corp, Bethpage, NY), and W R Neely, Jr (NASA, Langley Research Center, Hampton, VA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1295 19 p 10 refs A piloted simulator evaluation of the stability and control characteristics of a relaxed static stability fighter aircraft was conducted using a differential maneu- vering simulator The primary purpose of the simulation was to evaluate the effectiveness of the limiters in preventing departure from controlled flight The simulation was conducted in two phases, the first consisting of open-loop point stability evaluations over a range of subsonic flight conditions, the second con- centrating on closed-loop tracking of a preprogrammed target in low speed, high angle-of-attack air combat maneuvering The command limiters were effective in preventing departure from controlled flight while permitting competent levels of sustained maneuvering Parametric variations during the study included the ef- fects of pitch control power and wing-body static margin Stability and control issues were clearly shown to impact the configuration design C D A82-39083 # In-Flight investigation of large airplane flying qualities for approach and landing. N C Weingarten and C R Chalk (Calspan Ad- vanced Technology Center, Buffalo, NY) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1296 13 p 9 refs Contract No F33615-79-C-3618 A study of the handling qualities of large airplanes in the approach and landing Flight Phase was performed utilizing the USAF-AFWAL/Calspan Total In-Flight Simulator A one-million pound statically unstable airplane model was used as a 486 V \ A82-39100 baseline about which variations were made The primary variables were relative pilot position with respect to center of rotation, command path time delays and phase shifts, augmentation schemes and levels of augmentation The results indicate that the approach and landing task with very large airplanes is a fairly low bandwidth task I ow eouivalfint "shnrt-oenod frequencies and relatively long time delays can be tolerated As the pilot position is moved aft towards and then behind the center of rotation, pilot ratings are degraded (Author) A82-39084 * # Development and flight test evaluation of a pitch stabil- ity augmentation system for a relaxed stability L-1011. J J Rising (Lock- heed-California Co, Burbank, CA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1297 10 p 5 refs Contract No NAS1-15326 The L-1011 has been flight tested to demonstrate the relaxed static stability concept as a means of obtaining significant drag benefits to achieve a more energy efficient transport Satisfactory handling qualities were maintained with the design of an active control horizontal tail for stability and control augmentation to allow operation of the L-1011 at centers of gravity close to the neutral point Prior to flight test, a motion base visual flight simulator program was performed to optimize the augmentation system The system was successfully demon- strated in a test program totaling forty-eight actual flight hours (Author) A82-39085 # Supersonic missile aerodynamic and performance rela- tionships for low observables mission profiles. R J Krieger (McDonnell Douglas Astronautics Co , St Louis, MO) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1298 11 p 8 refs Closed-form analytical relationships are developed between supersonic mis- sile aerodynamic characteristics such as lift, zero-lift drag and drag due-to-lift and performance parameters such as range, velocity, specific range, flight path angle and maneuver load factor These relationships apply to low observable missile flight profiles for long range cruise and glide missions The analytical relationships are developed for climb, cruise, glide, dive, and run-in segments The results include equations for use in closed-form performance estimates and guiding configuration development (Author) A82-39090 * # Applications of parameter estimation in the study of spinning airplanes. L W Taylor, Jr (NASA, Langley Research Center, Hamp- ton, VA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1309 7 p 12 refs Spinning airplanes offer challenges to estimating dynamic parameters because of the nonlinear nature of the dynamics In this paper, parameter estimation techniques are applied to spin flight test data for estimating the error in measuring post-stall angles of attack, deriving Euler angles from angular velocity data, and estimating nonlinear aerodynamic characteristics The value of the scale factor for post-stall angles of attack agrees closely with that obtained from special wind-tunnel tests The independently derived Euler angles are seen to be valid in spite of steep pitch angles Estimates of flight derived nonlinear aerodynamic parameters are evaluate, in terms of the expected fit error (Author) A82-39091 * # Analysis of general-aviation accidents using ATC radar records. R C Wmgrove and R E Bach, Jr (NASA, Ames Research Center, Moffett Field, CA) American Institute of Aeronautics and Astronautics, Atmo- spheric Flight Mechanics Conference, 9th, San Diego CA Aug 9-11 1982 Paper 82-1310 8 p 12 refs It is pointed out that general aviation aircraft usually do not carry flight record- ers, and in accident investigations the only available data may come from the Air Traffic Control (ATC) records A description is presented of a technique for deriving time-histories of aircraft motions from ATC radar records The employed procedure involves a smoothing of the raw radar data The smoothed results, in combination with other available information (meteorological data and aircraft aerodynamic data) are used to derive the expanded set of motion time-histories Applications of the considered analytical methods are related to different types of aircraft, such as light piston-props, executive jets, and commuter turboprops, as well as different accident situations, such as takeoff, climb-out, icing, and deep stall G R large spin rates The results of this modified strip theory are shown to be in good agreement with spin tunnel rotary balance test data (Author) A82-39093 ' # A simple, low cost application of a flight test parameter identification system. R Clarke and J Roskam (Kansas, University, Lawrence, KS) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 32-1312 8 p 9 refs Grant No NsG-4019 The flight test system combines state-of-the-art microprocessor technology and high accuracy instrumentation with parameter identification technology which minimize data and flight time requirements The system was designed to avoid permanent modifications of the test airplane and allow quick installation It is capable of longitudinal and lateral-directional stability and control derivative esti- mation This paper presents details of this system, calibration and flight test procedures, and the results of the Cessna 172 flight test program The system has proven easy to install, simple to operate, and capable of accurate estimation of stability and control parameters in the Cessna 172 flight tests (Author) A82-39094 # Parameter estimation applied to general aviation air- craft - A case study. W R Wells (Wright State University, Dayton, OH) and V Klein (George Washington University, Washington, DC, Joint Institute for Ad- vancement of Flight Sciences, Hampton, VA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1313 12 p 27 refs NASA is currently involved in extensive general aviation stall-spin studies In undertaking the stall-spin research, the aircraft dynamics in pre and post stall regimes must be understood A case study is presented of the application of parameter estimation methods to problems of general aviation aircraft The re- search areas considered are related to control input selection, data compatibility, identification algorithms, unsteady aerodynamic modeling, and model structure determination Several recent advances in the application of systems identifica- tion are summarized using the aircraft as subject These advances are concerned with such techniques as stepwise regression algorithms, design of optimal control selection for parameter estimation, use of Kalman filtering in data compatibility checks, frequency domain identification algorithms, and high angle of attack formulation It is shown that the discipline of systems identification can be quite effective in improving the knowledge of the flight mechanics of general aviation aircraft G R A82-39098 * # Dynamic load measurements with delta wings undergo- ing self-induced roll-oscillations. D Levin and J Katz (Technion-lsrael Institute of Technology, Haifa, Israel) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1320 11 p 11 refs Grant No NAGW-00218 The aerodynamic forces acting on a delta wing, mounted on a free-to-roll sting-balance apparatus, were measured Two wing planforms having leading edge sweeps of 76 and 80 deg were tested, but only the wing with the 80 deg sweep would undergo periodic self-induced roll oscillation The time dependent forces and roll angles for this wing were then recorded for various test conditions In these tests a considerable drop in the average normal force of the free-to-roll wing was measured, relative to the normal force obtained in the static tests Also, the helium-bubble flow visualization technique was used to gam some insight into the periodic motion of the separated leading edge vortices (Author) A82-39099 * # High angle-of-attack characteristics of a forward-swept wing fighter configuration. S B Grafton, W P Gilber, M A Croom, and D G Murn (NASA, Langley Research Center, Hampton, VA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1322 19 p 13 refs The NASA-Langley Research Center is currently investigating the high angle- of-attack characteristics of a forward-swept wing fighter technology demonstra- tor in a cooperative program with the Defense Advanced Research Proiects Agency The program includes static and dynamic wind-tunnel force tests, free- flight model tests, spin-tunnel tests, and piloted simulation Particular emphasis is placed on identifying the contributions of the forward-swept wing to the configu- ration aerodynamics at high angles of attack Results are presented to illustrate the wing contributions in terms of aerodynamic stability, flow visualization, and observation of free-flight characteristics (Author) A82-39092 * # An estimation of aerodynamic forces and moments on an airplane model under steady state spin conditions. B N Pamadi and L W Taylor, Jr (NASA, Langley Research Center, Hampton, VA) American Insti- tute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1311 14 p 21 refs The problem of estimating the aerodynamic characteristics of a wing body configuration of a spinning airplane at extreme angles of attack and spin rates is approached by the application of strip theory Semiempincal methods are used to estimate the aerodynamic force distributions over each component using static, nonrotational wind-tunnel test data To these predictions, corrections are applied to account for the primary rotational flow effects which are significant at A82-39100 # The use of small strakes to reduce interference drag of a low wing, twin engine airplane. T E Wallis, D R Ellis (Cessna Aircraft Co , Wichita, KS), and W H Wentz, Jr (Wichita State University, Wichita, KS) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechan- ics Conference, 9th, San Diego, CA, Aug 9-11,1982, Paper 82-1323 13 p 5 refs This paper discusses the effect of small strakes on the interference drag of a low wing, twin engine airplane The strakes, highly swept delta wing semi-spans with a root chord 18 percent of the wing MAC, provide a strong streamwise vortex at high angles of attack They are placed on the fuselage and nacelles at the wing leading edge Both full scale and wind tunnel tests are discussed The strakes, in the proper location, provide a reduction in interference drag, increases in 487 A82-39102 maximum lift coefficient and lift to drag ratio at high angles of attack, a broader range of high lift coefficients, and less abrupt stall characteristics (Author) ration criteria, a longitudinal following model, longitudinal capture, combined longitudinal/vertical control, and lateral control G R A82-39102 * # Dynamic stability of flexible forward swept wing air- craft. T A Weisshaar and T A Zeiler (Purdue University, West Lafayette, IN) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechan- ics Conference, 9th, San Diego, CA, Aug 9-1 r, 1982, Paper 82-1325 12 p 25 rets Grant No NAG1-157 This paper describes potential vehicle instability modes for forward swept wing aircraft and other divergence prone aircraft Examples show that either body- freedom flutter or aircraft aeroelastic divergence may occur depending upon the airplane planform geometry and mass distribution These vehicle instabilities may occur at speeds very different than the clamped wing aeroelastic divergence speed (Author) A82-39103 # Optimal three-dimensional turning performance of su- personic aircraft. C -F Lin (Wisconsin, University, Madison, Wl) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Confer- ence, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1326 10 p 17 refs This paper discusses real-time, on-line three-dimensional turning maneuvers of supersonic aircraft with emphasis on the problems of minimum-time and mini- mum-fuel turns The minimum-time problem is completely solved For the mini- mum-fuel case, the problem of minimum-fuel turn to a line is solved while suggestions for further research on minimum-fuel turn in three dimensions are presented Two mathematical models of the aerodynamic and engine character- istics are designed to facilitate the application of the optimal control theory to analyze a wide range of flight programs One such model is a typical lightweight, high thrust-to-weight ratio fighter used for the computation of minimum-time prob- lem The other is a rocket-powered aircraft used for the computation of the minimum-fuel problem (Author) A82-39105 # The correlation of flight test and analytic M-on-N air combat exchange ratios. D S Hague (Aerophysics Research Corp , Bellevue, WA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1328 6 p Contract No F33615-80-C-3003 This paper compares analytic and flight test predictions of Many-on-Many air combat performance capability It is shown that stochastic effects dominate air combat encounter outcomes and that air combat performance estimates should be based on a large sample of encounters Overall exchange ratios, the number of red losses per blue loss, predicted by flight test and analysis are within 5% of each other Trends in exchange ratio with force size obtained by the two methods are also similar Finally, it is shown that air combat performance is sensitive to both force size ratio and the total number of aircraft engaged and that differences in performance between aircraft types may diminish with increasing aircraft numbers (Author) A82-39106 * # Unique flight characteristics of the AD-1 oblique-wing research airplane. R E Curry and A G Sim (NASA, Flight Research Center, Edwards, CA) American Institute of Aeronautics and Astronautics Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11 1982, Paper 82-1329 8 p 9 refs Flight characteristics associated with an oblique-wing airplane have been stud- ied with limited scope and complexity using the AD-1 research vehicle The AD-1 is a low-speed, low-cost, manned airplane with an aeroelastically tailored wing that can be pivoted 0 to 60 deg asymmetrically Results of the 'light tests include aerodynamic parameter extraction, verification of the aeroelastic wing design criteria, trim requirements, stall characteristics, and an evaluation of the handling qualities and basic control system requirements Some of the unique characteris- tics of these results that pertain to the oblique-wing design are presented (Author) A82-39107 * # Analysis of in-trail following dynamics of CDTI- equipped aircraft. J A Sorensen and T Goka (Analytical Mechanics As- sociates, Inc, Mountain View, CA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1330 10 p 14 refs Contract No NAS1-16135 In connection with the necessity to provide greater terminal area capacity, attention is given to approaches in which the required increase in capacity will be obtained by making use of more automation and by involving the pilot to a larger degree in the air traffic control (ATC) process It was recommended that NASA should make extensive use of its research aircraft and cockpit simulators to assist the FAA in examining the capabilities and limitations of cockpit displays of traffic information (CDTI) A program was organized which utilizes FAA ATC (ground- based) simulators and NASA aircraft and associated cockpit simulators in a research project which explores applications of the CDTI system The present investigation is concerned with several questions related to the CDTI-based ter- minal area traffic tactical control concepts Attention is given to longitudinal sepa- A82-39117 * # Flight dynamics of rotorcraft in steep high-g turns. R T N Chen (NASA, Ames Research Center, Moffett Field, CA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th. San Diego, CA, Aug 9-11, 1982, Paper 82-1345 16 p 21 refs An analyticl procedure developed to permit a systematic examination of rotor- - craft flight dynamics in steep high-g turns is presented The procedure is used in a numerical investigation of a tilt-rotor aircraft and three single-rotor helicopters that have different types of main rotor systems The results indicate (1) that strong coupling in longitudinal and lateral-directional motions exists for these rotorcraft in high-g turns, (2) that for single-rotor helicopters, the direction of turn has a significant influence on flight dynamics, and (3) that a stability and control augmentation system that is designed on the basis of standard small-disturbance equations of motion from steady straight and level flight and that otherwise performs satisfactorily in operations near 1 g, becomes significantly degraded in steep turning flight (Author) A82-39118 * # A ground-simulation investigation of helicopter decelerating instrument approaches J V Lebacqz (NASA. Ames Research Center, Moffett Field, CA) American Institute ol Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11. 1982, Paper82-1346 11 p 24 refs In connection with the expansion of civil helicopter operations in the current era. the effect of helicopter flight and control characteristics on the flying qualities for instrument flight rules (IFR) flight have become a factor of concern, and a re- search program has been initiated to investigate IFR certification criteria A de- scription is presented of an experiment which is the sixth in a series of ground- and flight-simulation investigations This piloted-simulator experiment was con- ducted to examine the influence of stability-control augmentation, display infor- mation format, and approach-task effects on helicopter flying qualities for terminal-area operations incorporating a deceleration in instrument meteorologi- cal conditions Simulated test configurations were evaluated for precision ap- proaches with an instrument deceleration from 60 to about 15 knots in both calm air and simulated moderate turbulence and wind shear G R A82-39119 # Maneuver stability of a vehicle with a towed body. B L Nagabhushan (Goodyear Aerospace Corp , Defense Systems Div , Akron, OH) and E M Cliff (Virginia Polytechnic Institute and State University, Blacksburg, VA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1347 9 p 8 refs Research supported by the Virginia Polytechnic Institute and State University Nonlinear equations of motion are derived and subsequently linearized to de- scribe the coupled dynamics of a vehicle with a towed body Using these stability of an aircraft with a sling load has been determined for simple maneuvers where the vehicle is maintaining a straight and level flight path or performing a steady turn The effect of orienting the corresponding thrust vector of the aircraft on the system stability is examined by considering the thrust (1) fixed in mertial space, (2) fixed with respect to the vehicle relative wind Typically, towing cable length, towed body to vehicle mass ratio, and load factor in a turn have been found to affect stability of the aircraft and its sling load These results are illustrated here with an example of a maneuvering helicopter with a sling load (Author) A82-39120 # Application of multivanable model following method to flight controller. K Kanai (Defense Academy. Yokosuka, Japan), P N Nikiforuk (Saskatchewan, University. Saskatoon, Canada), S Uchikado, and N Hon American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechan- ics Conference, 9th, San Diego, CA, Aug 9-11, 1982. Paper 82-1349 7 p The present investigation is concerned with the problem of designing a model following control system for a multivanable linear plant, taking into account an application to the synthesis of a multnnput multioutput flight controller Attention is given to a problem statement, the construction of a model following system via state feedback plus input dynamics, and the synthesis of a Control Configured Vehicle (CCV) controller It is found that the construction of a model following system via state feedback with input dynamics compensator becomes possible even for the case of the singular control matrix Using the proposed method. CCV modes, such as desirable precision maneuvers, independent velocity, and alti- tude changes, are achieved G R A82-39121 # Design and analysis of a multivanable control system for a CCV-type fighter aircraft. D B Ridgely, S S Banda (USAF. Flight Dy- namics Laboratory, Wright-Patterson AFB. OH), arid J T Silverthorn (USAF, Wright Aeronautical Laboratories and Institute of Technology, Wright-Patterson AFB, OH) American Institute of Aeronautics and Astronautics Atmospheric Flight Mechanics Conference, 9th, San Diego. CA Aug 9-11 1982 Paper 82-1350 8 p 10 refs The theory of high-gain, error-actuated feedback control was applied lo the design of a longitudinal decoupling flight control system for an advanced fighter 488 A82-39141 aircraft Because of the structure of the system, measurement variables different from the outputs are necessary to apply this method This paper describes how entire eigenstructure assignment can be used to determine appropriate measure- ment equations by assigning their corresponding transmission zeros A singular value decomposition was used to choose the eigenvectors from their permissible subspaces Proper selection of eigenvalues/eigenvectors was shown to be cru- cial to the successful application of this theory (Author) A82-39122 # An MLS with computer aided landing approach. M N Wagdi (Riyadh, University, Riyadh, Saudi Arabia) American Institute of Aeronau- tics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego. CA, Aug 9-11, 1982. Paper 82-1352 9 p 5 refs A computerized landing approach path definition that utilizes the MLS radio navigational aid is presented An algorithm is developed which identifies the minimum time path that connects the initial MLS engage point to the touch down point Such path is generally composed of two segments. The first segment begins at the MLS engage point and ends at the beginning of the straight glide slope The second segment starts at the beginning of the straight glide slope and ends at the touch down point The MLS azimuth and elevation and DME signals are processed by an on board computer that displays on a -CRT the aircraft position relative to the ideal position of the optimal computed landing pattern The present technique allows the initiation of landing approaches from wide range of headings and elevations, thus resulting into more efficient terminal area traffic control Also it is suitable for low visibility landing approaches (Author) A82-39123 # Perspectives of the flying qualities specification. S G Fuller and D J Moorhouse (USAF, Wright Aeronautical Laboratories, Wright- Patterson AFB, OH) American Institute of Aeronautics and Astronautics, Atmo- spheric Flight Mechanics Conference, 9th, San Diego. CA, Aug 9-11, 1982, Paper 82-1354 9 p 24 refs A combined flying qualities and flight controls conference was held to discuss proposed changes to MIL-F-8785C and MIL-F-9490D These changes were primarily due to the new MIL-Standard and Handbook format being developed A summary is presented of the formal and informal presentations and the discus- sions related to flying qualities topics Included are organization of the require- ments, equivalent systems, alternate criteria, atmospheric disturbance effects and the relationship of the flying qualities and flight control system requirements In recent years the flying qualities specification has lost credibility Results of this credibility loss and the solutions for the future are discussed (Author) A82-39124 # Guidance for the use of equivalent systems with MIL-F- 8785C. T A Gentry (USAF, Flight Dynamic Laboratory, Wright-Patterson AFB. OH) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1355 11 p 20 refs It is pointed out that handling qualities requirements for military conventional aircraft are specified in MIL-F-8785C, Military Specifications - Flying Qualities of Piloted Airplanes' This specification places requirements on the characteristics of the overall aircraft system as perceived by the pilot during piloted control An application of the specification in the case of conventional aircraft presents no difficulties However, there may be problems with more complex flight control systems In order to compare future augmented aircraft systems to MIL-F-8785C the equivalent system approach has been suggested The present investigation provides guidance in the application of the equivalent system approach to aug- mented aircraft longitudinal dynamics and similar application to lateral-directional dynamics where appropriate The equivalent of an augmented system is actually produced by matching the actual high-order system with an equivalent low-order system G R A82-39125 * # A modern approach-to pilot/vehicle analysis and the Neal-Smith criteria. B J Bacon and D K Schmidt (Purdue University, West Lafayette, IN) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference. 9th, San Diego, CA, Aug 9-11, 1932, Paper 82-1357 10 p Grant No NAG4-1 The present investigation is concerned with the development of a better pilot modelling technique via optimal control theory, taking into account concepts concerning 'pilot rating' considered by Neal and Smith (1970) The investigation conducted by Neal and Smith had the objective to provide data on the effects of Flight Control System dynamics and to develop a design criterion capable of pinpointing pilot problem areas encountered in performing a given task Neal and Smith devised a 'pilot-m-the-loop' analysis capable of showing problem areas in pitch attitude tracking Unfortunately the employed method has some drawbacks The current investigation attempts, therefore, to provide an alternate approach which makes use of an optimal-control pilot model An optimal control model (OCM) had been discussed by Klemman et al (1970) It is shown that the alter- nate approach, based on the OCM, offers some distinct advantages G R A82-39128 # Analysis and wind tunnel tests of a probe used to sense altitude through measurement of static pressure. K D Tillotson (General Dynamics Corp , Pomona, CA) and A E Fuhs (U S Naval Postgraduate School, Monterey, CA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1361 10 p 8 refs Navy-supported research A static pressure probe was tested to determine the feasibility of using the probe, as an integral part of a missile nose, to sense missile altitude Experiments were conducted at Mach 2 0 and at Mach 1 51 At Mach 2 0, the static pressure probe will perform within altitude specifications of 25,000 feet -I- or - 2,000 feet at angles-of-attack ranging from - 8 to + 8 degrees At Mach 2 0, within an angle-of-attack ranging from 0 to 6 degrees, the probe will measure free stream static pressure within 4 percent, a 4 percent error in measurement is equivalent to an altitude error of 900 feet The missile nose shock will remain downstream of the probe pressure ports for flight Mach numbers above 1 5 (Author) A82-39129 # Use of rotary balance and forced oscillation test data in six degrees of freedom simulation. J Kalviste (Northrop Corp , Hawthorne, CA) American Institute of Aeronautics and Astronautics, Atmosphenc Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1384 11 P New analysis techniques are presented that will blend the data from the rotary balance test, forced oscillation test and computed dynamic derivatives for a nonlinear 6 DOF simulation A component of the rotation vector about the velocity vector is used with the rotary balance test data The other components of the rotation vector are used with the forced oscillation test data and computed deriva- tives The problem of separating the pure rotational and acceleration terms of the forced oscillation test data is resolved Recommendations are made in the data reduction procedure for forced oscillation testing to make the results more usable for aircraft motion simulation (Author) A82-39132 # Close-coupled canard-wing vortex interaction and Rey- nolds stress acquisition. W Calarese (USAF, Wright Aeronautical Laborato- ries, Wright-Patterson AFB, OH) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1368 12 p 7 refs The present experiment investigates the interaction of canard and wing vortices and their effect on the lifting wing's flow field turbulence and Reynolds stresses Spanwise wing blowing was used to enhance, the leading edge vortex and alter the vortex trajectory in an effort to keep it locked to the wing's leading edge for lift enhancement The turbulence intensity and Reynolds stresses were obtained by using hot film anemometers Air blowing enhances the circulation over the wing, preventing extensive flow separation Reynolds stresses, mean velocity, and turbulence intensity values illustrate the vortex structure (Author) A82-39134 # Analysis of an airplane windshield anti-icing system. P Ross (Ross Aviation Associates, Sedgwick, KS) American Institute of Aeronau- tics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1372 8 p This report documents the analysis methods developed to predict the perform- ance of the windshield hot air anti-icing system on a business |et airplane Flight data gathered from dry air and natural icing tests are used to develop and verify the accuracy of a procedure that will predict the windshield surface temperature for either wet or dry air It is shown that windshield surface temperatures can be estimated to an accuracy of + or - 5% for a wide range of aircraft conditions It is demonstrated that the method is somewhat conservative for all conditions (Author) A82-3913S * # NASA Dryden's experience in parameter estimation and its uses in flight test. K W HiffandR E Maine (NASA, Flight Research Center, Edwards, CA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1373 16 p 17 refs An explanation of the parameter estimation method used at the Dryden Flight Research Facility is presented, and an overview is provided of experience related to the employment of this method, taking into account the utilization of this experi- ence in flight tests According to a definition of the aircraft parameter estimation problem, the system investigated is asumed to be modeled by a set of dynamic equations containing unknown parameters To determine the values of the un- known parameters, the system is excited by a suitable input, and the input and actual system response are measured The values of the unknown parameters are then inferred, based on the requirement that the model response to the given input match the actual system response Examples of parameter estimation in flight test are discussed, giving attention to the F-14 fighter, the HiMAT (high maneuverable aircraft technology) vehicle, and the Space Shuttle G R A82-39141 * # Effects of vortex breakdown on longitudinal and lateral- directional aerodynamics of slender wings by the suction analogy. C E Lan and C -H Hsu (Kansas, University, Lawrence, KS) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, 489 A82-39142 San Diego, CA, Aug 9-11, 1982. Paper 82-1385 17 p 30 refs Grant No NAG1- 134 A semi-empirical method based on the suction analogy is developed to predict longitudinal aerodynamics and lateral-directional characteristics of slender wings at high angles of attack, including effects of vortex breakdown The latter is based on a correlation parameter derived from the predicted leading-edge suction distri- bution in the attached flow Empirical formulas, derived from a least-square analysis of data, for the vortex-breakdown angle of attack at the trailing edge, the progression rate of breakdown points and the vortex lift recovery factor in the breakdown region are given Comparison of predicted results with data in lon- gitudinal aerodynamics and lateral-directional characteristics for wings exhibiting strong vortex flow shows that the present method is reasonably accurate Expla- nation for peculiar lateral-directional characteristics is given (Author) A82-39142 * # Lateral aerodynamics of delta wings with leading edge separation. J Katz (Technion - Israel Institute of Technology, Haifa, Israel) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechan- ics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1386 12 p 23 refs Grant No NAGW-00218 An unsteady vortex lattice method is presented for the calculation of the aero- dynamic forces acting on lifting surfaces undergoing complex three dimensional motion For the present case the nonsymmetric motion of a slender delta wing was considered and the resulting lateral characteristics were calculated The flow separation line was specified along the wing leading edge and the emanating vortex sheet shape and rollup was then calculated Numerical results are presented for the combined high angle of attack and side slip condition and for the wing constant roll and coning motions (Author) A82-39143 # Analytic extrapolation to full scale aircraft dynamics. L E Ericsson and J P Reding (Lockheed Missiles and Space Co , Inc , Sunnyvale, CA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1387 13 p 57 refs It is pointed out that the extrapolation from subscale wind tunnel data to full scale flight becomes an especially serious problem at subsonic speeds when stall is involved and at high subsonic and transonic speeds where shock-boundary layer interaction can dominate the aerodynamics In the case of dynamic testing, valid subscale simulation is often impossible A description is presented of an approach which provides a solution to this preliminary design dilemma The approach makes it possible to obtain a prediction of the full scale aircraft dynam- ics on the basis of an analytical extrapolation from subscale test data The considered procedure establishes analytic relationships between dynamic and static aerodynamic characteristics induced by viscous flow effects The veracity of the analytic method is proved by predicting dynamic test results using corre- sponding static test data at the same subscale flow conditions Finally, the proce- dure provides the input necessary for extrapolation to full scale G R A82-39190 Fixed pattern noise correction for staring arrays in guid- ance systems. D T Whmray (British Aerospace Public, Ltd , Co , Dynamics Group. Hatfield, Herts , England) In Advanced infrared detectors and systems, Proceedings of the Symposium, London, England, October 29, 30, 1981 (A82- 39176 19-35) London, Institution of Electrical Engineers, 1981, p 97-101 Infrared guided missiles of the next generation are expected to show significant advances in performance over those in current service These advances are partly related to an employment of focal plane arrays A size advantage is gained by the removal of the traditional scanning mirror and drive systems The introduc- tion of an electronic scanned array provides speed and reliability advantages and also the potential of increased sensitivity On the other hand, focal plane arrays do present their own set of problems in the areas of testing and operation The present investigation is concerned with some of the aspects of testing and sys- tems implementation of charge-coupled device (CCD) readout IR focal plane arrays which operate in the long wavelength atmospheric IR window A descrip- tion is presented of the principles of operation, and hardware techniques, which have been successfully used to achieve fixed pattern noise compensation at the high speeds necessary for focal plane arrays working in the long infrared wave- band G R A82-39191 Algorithm development for infra-red air-to-air guidance systems. P D Allen and J Northfield (British Aerospace Public, Ltd , Co , Dy- namics Group, Hatfield, Herts , England) In Advanced infrared detectors and systems, Proceedings of the Symposium, London, England, October 29, 30, 1981 (A82-39176 19-35) London, Institution of Electrical Engineers, 1981, p 102-111 General algorithms for the overall guidance of air-to-air infra-red missiles through the acquisition, tracking and terminal phases are described Special attention is given to the vital area of initial target detection Two 3x3 spatial operators are described and their response against naturally occurring cluttered sky images is reported An assessment of the performance of each of these operators as discriminators of simulated targets against cluttered backgrounds has been made and is reported The surprising result that point enhancement operators give impressive results even against large targets is discussed and qualified ' (Author) A82-39194 Target tracking using area correlation. R M B Jackson (EMI Electronics, Ltd , Hayes. Middx , England) (NATO, AGARD. Conference on Image and Sensor Data Processing for Target Acquisition and Recognition, Aal- borg, Denmark, Sept 8-12, 1980) In Advanced infrared detectors and systems, Proceedings of the Symposium, London, England, October 29, 30, 1981 (A82- 39176 19-35) London, Institution of Electrical Engineers, 1981, p 124-130 With the increasing use of electrooptical imagers in weapon systems'for air- craft, there is a need to provide an automatic track of targets of interest to relieve the operation - who may be the pilot - of this task A description is presented of a tracking system, based on the area correlator technique, which can provide a stable and accurate track of targets for use in airborne systems in conjunction with Forward Looking Infrared Radar (FLIR) or TV imagers It is of small size and can be built into standard format packages for installation in military aircraft The tracking system can handle targets with a wide range of characteristics, and it can adapt automatically to magnification and target aspect changes G R A82-39245 The system of 'objective control' (Das System der 'Ob- jektiven Kontrolle'). K -D Gratzsch (Interflug Gesellschaft fur Internationalen Flugverkehr mbH, Berlin, East Germany) Techmsch-okonomische Information der zivilen Luftfahrt, vol 18, no 1, 1982, p 1,2 In German The concept of 'objective control' was originally developed as a control proce- dure in connection with the failure of components and systems of aviation equip- ment However, it was soon recognized that this control method could also be employed for an evaluation of flight activities which is independent of subjective considerations This advantage and the possibility to analyze flights, on a routine basis and in a manner which cannot be foreseen by the involved persons, has considerable educational significance The system of 'objective control' in the case of a supervision of flight activities is based on the collection of information regarding the flight with the aid of onboard and ground-based equipment This system makes it possible to initiate corrective action as soon as shortcomings with respect to the activities of the flying personnel are recognized G R A82-39246 Rationalization of the maintenance process for heli- copter Ka-26 (Rationalisierung des Instandhaltungsprozesses fur Hubs- chrauber Ka-26). K Janeczek (Interflug Gesellschaft fur Internationalen Flugverkehr mbH, Leipzig, East Germany) Techmsch-okonomische Information der zivilen Luftfahrt, vol 18, no 1.1982, p 3-7 In German Since 1970, the helicopter Ka-26 has been employed in the mountainous areas of the German Democratic Republic for agricultural applications The mainte- nance program is a vital part of the utilization of the helicopter The information obtained in connection with the use of the helicopter provided an indispensable basis for an efficient, cost-effective organization of the maintenance procedures The enhancement of the efficiency of maintenance operations made it possible to increase the performance provided by the helicopter and to improve its reliabil- ity Attention is given to the conventional maintenance system for helicopter Ka-26, the requirements for an optimization of maintenance procedures for the helicopter in agricultural applications, the development of an optimal mainte- nance system, and the introduction of suitable control procedures G R A82-39247 Minimization of the total costs incurred in the employ- ment of passenger jet aircraft (Mmimierung der Gesamtkosten beim Em- satz von Strahlverkehrsflugzeugen). J Wilde (Interflug Gesellschaft fur Internationalen Flugverkehr mbH. Leipzig, East Germany) Techmsch-okonomis- che Information der zivilen Luftfahrt, vol 18, no 1,1982, p 8-14 In German A description is presented of a procedure which makes it possible to minimize the total costs for the flight of a |6t airliner The procedure makes use of an optimization method which attempts to take into consideration all factors that affect the costs of a flight The optimization problem is discussed, taking into account the various factors which affect fuel consumption and flight time, the determination of the Mach number which will provide a cost minimum, the consid- eration of meteorological factors and flight path characteristics, and the computa- tion of fuel consumption An investigation regarding the accuracy of the optimization calculation is also conducted After the completion of a calculation including an optimization, it is possible to determine fuel consumption, flight times, and total costs for arbitrary Mach numbers by making use of the data stored in the computer as a result of the preceding calculation Possible cost reductions for the operation of Interflug airliners are discussed, taking into account also the price for fuel at specific airports G R A82-39248 Instrument landing systems /ILS/ at airports of the Ger- man Democratic Republic (Instrumentenlandesysteme /ILS/ auf DDR- Flughafen). W Trempler (Interflug Gesellschaft fur Internationalen Flugverkehr mbH, Leipzig, East Germany) Techmsch-okonomische Information der zivilen Luftfahrt, vol 18, no 1,1982, p 15-20 In German The introduction of a new generation of landing systems of the type ILS SP-70 490 A82-39374 (System Posadki-70), provided by the Soviet industry, began with the installation of the first system of the considered type at the airport Berlm-Schonefeld in 1978 Up to March 1981, three more ILS SP-70 were installed at airports of the German Democratic Republic The utilization of the new SP-70 systems in Berlin and Leipzig has led to an improvement of aspects of flight safety for all arriving aircraft particularly under conditions of bad weather The SP-70 is suited for automatic approaches according to the standards of the ICAO Details concerning the ILS principles are discussed along with the characteristics of the ILS SP-70 The ILS SP-70 utilizes the most modern technology to satisfy Category III requirements Attention is given to ground installations, functional descriptions of system com-^ ponents, and antenna diagrams ' G R A82-39263 t The effect of hybrid composite materials on the dy- namic characteristics of helicopter rotor blades (Vliianie gibridnykh kom- pozitnykh matenalov na dinamicheskie kharaktenstiki lopastei vertoletov). E G Pak, V N Stekol'nikov, lu P Ganiushkm, R V Ivanmkova, and V N Kestel'man Mekhanika Kompozitnykh Matenalov, May-June 1982, p 475-479 7 refs In Russian It is shown that changes in the relationship between the rigidity and mass characteristics of helicopter rotor blades can be effected by varying the modulus of elasticity of the structural material of the spar Hybrid composite materials . make it possible to achieve this by combining in one matrix several reinforcing fillers with different physical and mechanical properties The optimal combination is that of glass and carbon fibers The carbon-and-glass-remforced plastic makes it possible to increase the rigidity of the spar without changing the mass charac- teristics as well as to increase the fatigue strength B J , A82-39275 Application of an optical data link in the airborne scan- ning system. M J Green (Wisconsin, University, Madison, Wl) Review of Scientific Instruments, vol 53, Aug 1982, p 1278-1280 A scanning thermal IR radiometer has been used in the acquisition and digital processing of thermal imagery In connection with plans for a study of oceanic thermal fronts, attention has been given to the possibility to employ the scanner in a system for mapping sea surface temperature which could be used with the Navy P-3 patrol aircraft The mam obstacle to such an employment is that, since the aircraft are to be used on an 'aircraft-of-opportunity' basis, no modifications to the aircraft would be permitted The scanner is comprised of two principal subsystems, including the scanner head itself and a power supply/signal condi- tioning chassis These two units are normally connected by a 39-conductor cable As the requirements regarding the Navy application do not permit an employment of the normal connection, an optical data link has been fabricated which can replace the hard-wired connections between scanner head and power supply GR A82-39279 t Primary-data devices (Pribory pervichnoi informatsu). V A Bodner Moscow, Izdatel'stvo Mashinostroenie, 1981 344 p 29 refs In Russian The work examines the theoretical principles, design, and analysis of primary- data devices, i e , sensors that are used to acquire information necessary for the control and monitoring of flight vehicles Particular consideration is given to ad- vanced measurement techniques (pulse-time and frequency output devices, cor- relation devices, etc ), the computer-aided design of the devices with allowance for complex optimization, the use of microprocessors, and automatic error com- pensation Attention is given to sensors for measuring pressure, temperature, fuel' consumption, flight speed and altitude, and acceleration B J A82-39295 t The operation of aircraft and helicopters in difficult meteorological and environmental conditions (Ekspluatatsna samoletov i vertoletov v uslozhnennykh pnrodnykh usloviiakh). A M Volodko Moscow, Izdatel'stvo Transport, 1981 158p 48 refs In Russian The effects of such adverse phenomena as turbulence, ice formation and hail, wind shear, and lightning on the operation of aircraft are considered Attention is also given to the effects of high and low air temperatures, dust in the air, and air moisture Biological damage (from microorganisms, insects, and birds) is also considered along with conditions of helicopter flight in mountain areas and clouds BJ A82-39321 Flight management computers (Calculateurs de gestion. du vol). J Grossm (Society Nationale Industnelle Aerospatiale, Toulouse, France) L'Onde Electnque, vol 62, June-July 1982, p 59-66 11 refs In French Flight management computers (FMC) and their role in reducing fuel consump- tion in commercial aircraft are examined Research to offset rising fuel costs is concentrating on improving engine efficiency and the aerodynamic performance of the aircraft, and in flight control computers which automate control of flight and systems to the most efficient levels Implementation of FMC with the Airbus is described, including the retrofit to provide accurate navigation and economical ascent and descent Flight time at low speed and altitudes is minimized, and systems surveillance and fuel flow are automated Block diagrams are presented of the systems interconnections with the FMC and the control strategy Flight plans fed into the FMC yield an optimized flight strategy based on a plan involving lowest cost The flight is categorized into ascent, cruise, and descent phases Constraints which can alter the plan consist of changes in altitude to maintain proper cruise speed, the tempo of the flight in reaching fixed ground reference points, and operational limits of the aircraft M S K A82-39322 Electronic stabilization of an aircraft (Stabilisation d'un avion par I'electronique). A Chadeau (Mmistere de la Defense, Service Tech- nique des Telecommunications et des Equipements Aeronautiques, Pans, France) L'Onde Electnque, vol 62, June-July 1982. p 67-71 In French The applications of electronic flight control systems (EFC) to the amelioration of engine troubles and to automatic pilot systems are reviewed Nominal instabili- ties are automatically corrected in-flight through commands implemented by electrohydraulic servocontrols responding to preset tolerances for the flight en- velope parameters, including airspeed, altitude, pitch, route, and landing func- tions EFC systems permit the use of aircraft configurations which experience instabilities which could not be handled by a human pilot, but can be electronically altered so that control of the aircraft appears similar to simple mechanical link- age Digitized control of a modern aircraft is noted to require over 400,000 operations/sec, with control decisions being weighted toward safety through calculations of the probability of occurrence of destabilizing events and an as- sessment of the total effect a command decision will have on the aircraft It is concluded that progress toward introducing new control stragegies is slow, in order to maintain the accuracy and operability of preexisting systems M S K A82-39323 Air-air collision avoidance systems (Systemes d'an- ticolhsion air-air). A Michel (Direction Generale de I'Aviation Civile, Service Technique de la Navigation Aenenne, Pans, France) L'Onde Electnque, vol 62, June-July 1982, p 72-82 10 refs In French Methods of improving air-to-air collision avoidance through ground based ac- tions are asserted to reside in flow control, by restricting the number of flights to levels which can be handled by available controller personnel aided by comput- ers and radar An on-board collision avoidance system is offered as a means to ameliorate the workload on the ground The systems tested thus far have oper- ated between 1520-1620 MHz and work multilaterally, obtaining identification of nearby aircraft, their relative distance, altitudes, and characterizing their ap- proach paths Attention is given to various systems developed as prototypes for operational systems, noting that the FAA is requiring that any system used be compatible with ATC Characteristics of the Discrete Address Beacon System introduced in 1980 are presented, including methods for the suppression of er- roneous data Problems in perfecting the control logic for the detection systems are discussed M S K A82-39358 # The unsteady motion of a wing traveling at subsonic speed above a plane (Neustanovivsheesia dvizheme kryla s dozvukovoi skorost'iu nad ploskost'iu). E A Krasil'shchikova Revue Roumame de Math- ematiques Pures et Appliquees, vol 27, no 3, 1982, p 363-370 In Russian An analysis is presented of the plane-parallel flow of a compressible fluid excited by a thin wing moving at subsonic speed above a plane, the motion of the wing taken to begin from a state of rest The aerodynamic problem is viewed as a combination of boundary value problems with a moving boundary for the two- dimensional wave equation Each of these problems is solved by the method of integral equations in characteristic coordinates The velocity potential is repre- sented in recursive formulas, which make it possible to analyze the interaction of the wing and plane for arbitrary moments of time B J A82-39359 # The rectangular wing with semimfinite span in nonlinear theory (Der rechteckige flugel halbunendhcher spannweite in der nichtlin- earen theorie). S Turbatu (Bucuresti, Universitatea, Bucharest, Rumania) Re- vue Roumame de Mathematiques Pures et Appliquees, vol 27, no 3, 1982, p 419-422 10 refs In German In an investigation of unsteady flow, use is made of an approach considered by Teipel (1964), Hosokawa (1964), and Ruo (1974) It is assumed that unsteady effects are superimposed on steady flow, taking into account a consideration of these effects in the first order The concepts employed in connection with the solution of the nonlinear differential equation are similar to those used by Os- watitsch and Keune (1955) for the steady flowfield A boundary-value problem in two parts regarding the potential of a rectangular wing with semimfinite span in a state of harmonic oscillations is also solved, taking into consideration the case of unsteady transonic flow in a nonlmeanzed treatment G R A82-39374 Optimal control application in supersonic aircraft per- formance. C -F Lin (Michigan, University, Ann Arbor, Ml) IEEProceedings, Part D - Control Theory and Applications, vol 129, pt D, no 4,July1982,p 113-117 In the present investigation, the aerodynamic and engine characteristics of a typical lightweight high thrust/weight ratio fighter are modelled as continuous functions of a state variable, the Mach number This approach provides the possibility for a smooth application of optimal control theory By introducing a set of dimensionless variables, general results are obtained for an entire class of vehicles with similar physical characteristics Numerical solutions are presented 491 A82-39399 to show the characteristics 01 the optimal trajectory, taking into account the optimal control features for guiding the aircraft along a particular trajectory A description is presented of the general properties of optimal trajectories These properties are used to solve any particular optimal trajectory which depends on the terminal conditions and the physical constraints G R A82-39399 t Application of the sequential optimization method to the tuning of the natural frequencies of gas-turbine engine compressor blades (Primenenie metoda posledovatel'noi optimizatsii k ostroike chas- tot sobstvennykh kolebanu lopatok kompressora GTD). A B Roitman, V P Afanas'ev, T F Mikhailova, and S P Omel'chenko Problemy Prochnosti, July 1982, p 86-89 5 refs In Russian The optimum tuning of the natural frequencies away from the dangerous reso- nance range is carried out for laterally oscillating turbine blades using the max- imum blade profile thickness as the control function The control range is limited by the tolerance on the blade geometry A quality functional is obtained which provides a way to tune the natural frequencies with allowance for the constraints involved V L A82-39403 t Problems in the simulation of correlation-extremal navi- gation systems (Problemy modelirovaniia korreliatsionno-ekstremal'nykh sistem navigatsii). V I Alekseev and V P Tarasenko (Tomskn Institut Av- tomatizirovannykh Sistem Upravlenna i Radioelektroniki, Tomsk, USSR) Elek- tronnoe Modehrovame, vol 4, July-Aug 1982. p 80-83 9 refs In Russian A general scheme for the simulation of correlation-extremal navigation sys- tems is described, and problems of the synthesis and analysis of these systems which can be implemented through hybrid computers are examined Applied programs developed for the simulation of correlation-extremal navigation sys- tems are briefly characterized B J A82-39404 t Simulation of correlation-extremal receivers of signals from sampling-phase radio-navigation systems (Modelirovanie korreliat- sionno-ekstremal'nogo pnemnika signalov impul'sno-fazovykh ra- dionavigatsionnykh sistem). I M Egorov and A M Korikov (Tomskn Gosudarstvennyi Universitet, Tomsk. USSR) Elektronnoe Modelirovame, vol 4, July-Aug 1982, p 84-89 6 refs In Russian The paper examines the simulation of correlation-extremal navigation systems according to radio fields created by sampling-phase radio-navigation systems Particular attention is given to the simulation software, and the synthesis of a correlation-extremal receiver is considered for a Loran-C type system B J A82-39467 t The use of analog computers in solutions of inverse problems of heat conduction for the identification of boundary conditions on the surfaces of gas-turbine-engine parts on the basis of temperature- measurement results (Ispol'zovanie AVM v resheniiakh obratnykh zadach teploprovodnosti dha identifikatsn granichnykh uslovn na poverkhnos- tiakh detalei GTU po rezul tatam ikh termometrirovaniia). B D Bileka, V N Klimenko, and S M Chepaskma (Akademiia Nauk Ukramskoi SSR, Institut Tekh- nicheskoi Teplofiziki, Kiev, Ukrainian SSR) Promyshlennaia Teplotekhnika, vol 4, July-Aug 1982, p 53-59 5 refs In Russian Methodological features and computational results are considered for two types of inverse problems of heat conduction without heat removal in the inner zone and with heat removal The first case is illustrated by the nonstationary problem of determining convective heat transfer from the gas to the stator above moving blades and to noncooled moving blades, while the second case is illus- trated by the stationary problem of determining convective heat transfer from the gas to cooled nozzle blades These two problems are treated by analog computa- tion on the basis of the finite difference method, an implicit scheme using the Liebman method is applied to the nonstationary problem Errors arising in the use of this approach to solve inverse heat-conduction problems are examined B J A82-39482 t Turbulent boundary layer on a porous surface with in- jection at various angles to the wall (Turbulentnyi pogranichnyi sloi na poristykh poverkhnostiakh pn vduvakn pod raznymi uglami k stenke). V M Eroshenko, A A Klimov, and L S lanovsku Akademiia Nauk SSSR, Izvestna, Mekhamka Zhidkosti i Gaza, May-June 1982, p 59-64 13 refs In Russian Experimental results are presented on turbulent boundary layers on porous plates in the case of uniform injection directed at various angles to the wall (15, 25,40,75, and 90 deg) The data disclose the influence of the intensity and angle of injection on the profiles of averaged and fluctuating velocities, charactenstic thicknesses, surface friction, and turbulent shear stresses in the boundary layer It is shown that moderate injections at angles to the flow are more effective in terms of protecting the surface than the commonly used normal-incidence injec- tion B J A82-39539 'Listening' systems to increase aircraft structural safety and reduce costs. C 0 Bailey and W M Pless (Lockheed-Georgia Co , Mari- etta, GA) Lockheed Horizons, Summer 1982, p 17-22 Applications of acoustic emissions (AE) techniques to in-flight monitoring of fatigue stresses leading to parts failure is discussed Due to inherent difficulties in designing all flows out of an aircraft, the deficiencies present in visual inspec- tion, and the existence of many hard-to-reach critical areas, the use of AE lor lifetime surveillance of potential fatigue-prone components of aircraft is offered as ah effective means to prevent failure Piezoelectric or capacitive devices are employed to detect AE originating from corrosion, stress-corrosion cracking, and crystal dislocation movements The sensors are tuned to ranges outside of nor- mal structural vibration and situated in areas known for potential flaws, some- times in arrays which serve to locate a flaw through tnangulation Performance on board the KC-135 aircraft is cited as evidence tor the cost-effectiveness of AE stress monitoring M S K A82-39S40 The fourth dimension. R L Heimbold and M f Leffler (Lockheed-California Co , Burbank, CA) Lockheed Horizons, Summer 1982, p 24-30 Problems and solutions for introduction of the Lockheed four-dimensional (4-D) flight management system (FMS) into regular airline traffic are explored The 4-D system is operated totally by the flight management computer, which directs the plane to appropriate altitudes and speeds for minimum fuel consumption over the entire flight The altitude is increased as fuel is consumed and the aircraft becomes lighter Integration of the system into current air traffic involves including accurate wind data, initial estimates of arrival time and options for the flight path, a sufficient capacity for ATC control metering and spacing procedures, and accuracy of high enough order to reduce ATC workloads Flow integration pro- ceeds 100 mi from the airport and the necessity for a holding pattern results in a revectonng for approach once a go-around has been completed It is noted that NWS forecasts are inadequate in terms of accuracy of available wind data M S K A82-39718 The technological aspects of titanium application in the TU-144 aircraft structure. S A Vigdortchik and A N Tupolev In Titanium and titanium alloys Scientific and technological aspects Volume 3 (A82-39626 19-26) New York. Plenum Press, 1982, p 2181-2193 The development of techniques leading to the construction of significant por- tions of the TU-144 aircraft with titanium alloys is reviewed Statistical data from experiments indicated that hydrogenation of the structural material and subse- quent slow-rate failures could be controlled by vacuum low-temperature anneal- ing, in addition to chemical milling combined with refining The relationship of nitrogen and oxygen surface content introduced by heating, cutting, and mul- tilayer welding to fatigue, slow-rate failure, and creep were also established statistically Automatic inert-gas welding in sealed chambers was found to control the failure-producing elemental contents Carbon contamination of surface layers was reduced by chemically etching and removing 0 2-0 5 mm of the surface Finally, salt-stress corrosion was determined to be minimal in the expected oper- ating temperatures of the titanium materials MSK A82-39727 Remotely piloted vehicles; International Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Papers and Supplemen- tary Papers. Conference sponsored by the Royal Aeronautical Society ^ and University of Bnstol Bristol, England, University of Bristol. 1982 Conference papers, 172 p, Supplementary papers, 57 p (For individual items see A82-39728 to A82-39750) Advances in system components, performance, and sensor systems of remotely piloted vehicles and unmanned vehicles are reported The impacts and applications of RPVs on combat situations and costs are discussed, along with the various configurations of fixed wing and helicopter platforms, and Canadian, Bntish, and U S efforts in RPV developmental programs Attention is given to the various sensors which an RPV may carry, including radar, TV cameras, IR scan- ners, radiometers, and dead reckoning guidance systems The design of al- gorithms for terrain following systems is described, as are sensor stabilization requirements and images received from remote sensors Attention is given to the use of radio controlled aircraft in pollution studies, propulsion systems for RPVs, and image orientation for RPV ground station crew members MSK A82-39728 # Unmanned aircraft in future combat. W D Simpson (Brit- ish Aerospace Public, Ltd, Co , Dynamics Group, Stevenage, Herts , England) In Remotely piloted vehicles. International Conference, 2nd. Bristol. England, Apnl 6-8.1981, Conference Papers (A82-39727 19-01) Bristol, England, Univer- .sity of Bnstol, 1982, p 21-25 An assessment of the total effect of unmanned vehicles on armed forces is presented The U S Army Aquila is noted to provide reconnaissance capability in a fixed wing aircraft form, while tethered helicopter platforms and drone dirigi- bles show promise of fulfilling the same needs at lower cost Explosives delivery to targets at a distance have reached the level of cruise missiles, which are completely dependent on internal sensors and processors once launched Simi- lar autonomous vehicles, piston engmed, can be used to jam radar, dispense chaff, and are called harassment drones Production costs increase with the degree of sophistication of the system, including addition of IR sensors, jam-free radio, and personnel training required for control and retneval The autonomous 492 A82-39738 systems are nominally used in large numbers and fly at high altitudes to retain hne-of-sight communications MSK A82-39729 # Horses for courses in RPV operations. R G Austin and C J Roberts (ML Aviation Co , Ltd , Bristol,.England) In Remotely piloted vehi- cles, International Conference, 2nd, Bristol, England, April 6-8,1981, Conference Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 3.1-318 Different configurations and capacities, the increase of cost with complexity, and examples of RPVs are examined The highest cost savings engendered by use of RPVs is noted to be the stationing of the pilot in a relatively benign environment, while additional benefits are gained from civilian applications such as crop spraying and pollution monitoring, a smaller target in combat situations, and the reduction in support crew necessary for military applications Although the range is generally limited to a quarter mile from the controller, repeated flights may be made for photographic purposes Operation and components of a mini- mal system are described, and means of extending the range, addition of a TV camera, uses of helicopter-type vehicles, and retrieval by netting are reviewed Attention is also given to equipping RPVs for flight in severe weather, reduction of noise, shielding the RPV IR emissions, and standards for the production of RPVs M S K A82-39730 # Short range tactical RPH system. M J Breward (West- land Helicopters, Ltd , Yeovil, Somerset, England) In Remotely piloted vehicles, International Conference, 2nd, Bristol, England, April 6-8,1981, Conference Pa- pers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 41-412 5 refs Design features of a remotely piloted helicopter (RPH) for use in surveillance and as an observation post are discussed The RPH is intended for use in the forward combat zone and needs high mobility, rapid deployment, flexibility of response, and rapid response Performance requirements include all weather operation, 24-hr capability, a 10-km radius of action, a response time less than 10 mm, and real time data flow Attention is given to the sensor system with look-up ability, using low-light TV or IR scanner The characteristics of the Wisp and Wideye RPHs are described,'including payloads of 30 and 25 kg, respec- tively, and all up weights of 125 and 85 kg Command links are achieved with low frequency transmissions lasting short periods, with 30-60 sec intervals of silence Dead reckoning with meteorological input alone is recommended for overcoming the dangers of ECM M S K A82-39731 # Canadair rotary wing technology development. A S Clark (Canadair, Ltd , Montreal, Canada) In Remotely piloted vehicles, Interna- tional Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 5 1-5 13 Design, performance, and operational features of the Canadair CL-227 rotary wing RPV are detailed The CL-227 is intended as a surveillance and target acquisition system transmitting in real time, operating in the short-to-medium range battlefield locations, and controlled by mobile units A rotary winged con- -.figuration permits take-off from unprepared ground and hovering over target -'areas The vehicle is modular in design, comprising power, rotor, and control iumts A Wankel engine has been successfully employed during testing, and rotor blades are made of Kevlar with a foam core The control module contains.sensor - and telemetry equipment for microwave relay and operation with four degrees of freedom Attention is given to the development of a transfer function suitable for maintaining the aerodynamic stability of the vehicle A total of 300 flights had been performed by 1980, and test procedures are described M S K A82-39732 # U.S. Army remotely piloted vehicle program. J K Mar- stiller (U S Army, Aviation Research and Development Command, St Louis, MO) In Remotely piloted vehicles, International Conference, 2nd, Bristol, En- gland, April 6-8, 1981, Conference Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 6 1-6 5 The U S Army full scale engineering development program for the Aquila RPV is described Aquila is intended as an artillery aid to provide target acquisition, permit first round fire for effect, allow artillery adjustment, and provide designa- tion for laser guided projectiles out to maximum'artillery range The entire system comprises the air vehicle, a ground control station, remote ground terminal, 'a hydraulic catapult launcher, a net type recovery subsystem, and suppo'rt,equip- ment Aquila is launched 10-15 km on the friendly side of combat lines and flight is governed by preprogrammed internal commands covering waypdints, with loiter or jinking modes available by remote control, received in burst form The vehicle carries a stabilized TV sensor with laser rangefmder/designator, and is constructed to survive in nuclear, ballistic, and chemical environment's,; and in worldwide climatic conditions Operational testing is scheduled for 1982 ' - M S K (A82-39727 19-01 (Bristol, England, University of Bristol, 1982, p 7 1-7 12 6refs Performance, design, and materials characteristics of the Stabileye RPV, which is used to define applications of RPVs, are detailed The Stabileye has progressed through three versions, each featuring a twin-boom pusher engine layout, with the most recent, the MK 3, carrying a maximum payload of 25 kg, a 50 m/sec or less top speed, and flight duration of one hour The MK 3 was constructed to examine the effectiveness of glass reinforced plastics and honey- comb core material for the fuselage, bulkheads, nose and rear body fairings, and the top lid, which conceals the payload and recovery parachute The wing is a NACA 4415 profile made of hot-wire cut polystyrene foam with multiple hardwood spars and wood veneer/glass reinforced plastic skins A two-cylinder, 7-hp power plant is interfaced with a pulse code modulated system The primary sensor is a vertical gyroscope, with flight control electronics, a yaw rate gyro, and a telemetry encoder MSK A82-39734 # The national dynamics 'observer' mini-RPV for tropical operation. M Reed (Natal, University, Durban, Republic of South Africa) In Remotely piloted vehicles, International Conference, 2nd, Bristol. England, April 6-8,1981, Conference Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 91-99 7 refs Results of testing program of a mini-RPV for civil and military applications in South Africa are reported The airframe was fabricated using epoxy resm/fiber- glass and fire-retard low density styrofoam A two-stroke engine was chosen, developing 22 6 hp at 7200 rpm and a four-bladed propeller for reasons of maintaining engine speed Launch is from the roof of a car and power for servo- units is derived from nickel-cadmium battery packs Program goals for additional development of a rhombic-wing mini-RPV are outlined MSK A82-39735 # MACHAN - A unmanned aircraft flight research facility. T G Hamill (Marconi Avionics, Ltd , Rochester, Kent, England) In Remotely piloted vehicles, International Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 101-108 Research supported by the Ministry of Defence (Procurement Executive) The purpose of this paper is to introduce the MACHAN programme, or to give it it's full name, 'the provision of an unmanned aircraft flight research facility' This programme is funded by MOD(PE) with a substantial PV input from Marconi Avionics ,The 3 aspects of the programme covered are the aircraft itself, the supporting facilities and, here, specifically the ground station, and the programme of experimental flying and payload trials as it is currently envisaged (Author) A82-39736 # Mini-RPV propulsion. L A Kolbo (Kolbo Corp , Anaheim, CA) In Remotely piloted vehicles, International Conference, 2nd, Bristol, En- gland, April 6-8, 1981, Conference Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 13 1-134 Mini-RPV propulsion systems which can deliver flight durations of four hours at speeds between 100 and 200 kn are reviewed The reciprocating internal combustion engine is the favored choice because of fuel density, noise, heat signature, and fuel consumption characteristics A two-cylinder configuration is the most satisfactory choice due to lightness, carburation, and simplicity The engine components are preferably made of aluminum, chromium, and aluminum- magnesium alloys to preserve weight-saving design goals and heat-tolerant properties It is recommended that mim-RPVs have a specific fuel consumption of 0 8, with an aneroid barometer-equipped carburetor in order to adjust fuel-air mixtures for height automatically An ignition system which delivers 40,000 V open circuit is described, and features of propellers are discussed in terms of performance and material considerations MSK AB2-39737 # The application of small propellers to RPV propulsion. A C Roberts (British Aerospace Public, Ltd , Co , Dynamics Group, Bristol, England) In Remotely piloted vehicles, International Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Papers (A82-39727 19-01) Bristol, En- gland, University of Bristol, 1982, p 14 1-14 10 Progress in the development of a data base for construction of propellers for increasing the range and performance of small unmanned aircraft is assessed Compromises are necessary in design of propellers due to different requirements during climb and dash flight modes, and options for areas to explore include diameter and number of blades Restrictions include resulting size of the radar target produced, the effect on forward looking sensors, recovery method, and noise Small RPV propellers operate in the middle of the critical Reynolds number flow regime, encountering both laminar and turbulent flows while turning at 6000-8000 rpm A numerical model is developed for optimizing propeller effi- ciency and a computer program is outlined for predicting performance Wind tunnel tests of 0 5 m diam fixed-pitch 2-blade propellers showed that current predictions degrade in accuracy with increases in forward speed MSK A82-39733 # Stabileye. R Stephenson (British Aerospace Public, Ltd , Co , Dynamics Group, Bristol, England) In Remotely piloted vehicles, Interna- tional Conference, 2nd, Bristol. England, April 6-8, 1981, Conference Papers A82-39738 # The control and guidance unit for MACHAN. I F Cooper and J A Birkenshaw (Marconi Avionics, Ltd , Rochester, Kent, England) In Remotely piloted vehicles, International Conference, 2nd, Bristol, England, April 493 A82-39739 6-8,1981, Conference Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 161-1611 Research supported by the Ministry of Defence (Procurement Executive) Details of the MACHAN development program for evaluating the unmanned aircraft guidance achievable by a dead reckoning system aided by other systems and sensors are presented An attitude and heading reference (AHRS) system was concluded to require a vertical reference within 0 5 deg and a heading reference of not more than 4 deg/hr, provide pitch, roll, and yaw rates for the autopilot, operate digitally, possess navigation capability and update, operate within various mission profiles, and be amenable to mass production The AHRS system constructed featured three single axis gyros, three accelerometers, a dedicated real time microprocessor, and attitude recognition by reference to gravity and initial data supplementary sensors, such as a single degree of free- dom rate integrating gyro and accelerometer, pass data through the micro- processor where magnetic heading and Doppler' velocity data are also considered M S K A82-39739 # US. Army remotely piloted vehicle supporting tech- nology program. T D Gossett (U S Army, Research and Technology Labora- tory, Moffett Field, CA) In Remotely piloted vehicles, International Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 181-1810 10 refs Details of the U S Army full scale engineering development program for the RPV Aquila are described The system includes the air vehicle, a recovery sys- tem, an air vehicle handler, a remote ground terminal, a ground control station, a launcher subsystem, and a maintenance shelter With attention focused on the propulsion and antijam data link developments, it is noted that the data link includes a command uplink, telemetry downlink, video downlink, and navigation of the air vehicle relative to the remote ground terminal Components of the antijam modular integrated communication and navigation system comprise an analog null steerer, modems with chopped chirp waveforms, a direct pseudo- noise spread modem, and a phased array Ducted propellers were determined to offer higher takeoff, and quieter performance and efficiency than open propel- lers Finally, operational features of the 20 hp test engines and the FUR sensor are provided M S K A82-39740 # A terrain following system, an algorithm and a sensor. E Skarman (Saab-Scania AB, Lmkoping, Sweden) and U Rehammar (Telefonak- tiebolaget L M Ericsson, Molndal, Sweden) In Remotely piloted vehicles, Inter- national Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 191-1915 The development of a control logic for terrain following RPVs using radar and laser sensors to detect possible obstacles at least 1300 m in advance is de- scribed analytically Limitations in the theory of linear dyn ic systems are dis- cussed in terms of filtering an input command with a low pass filter to avoid exceeding the mechanical environment stress limits of all vehicle subsystems The odelmg of a dynamic system comprises two states of the kinematics, vertical speed and altitude, the two states pitch of the vehicle dynamics, the flight control system, which is an acceleration feedback system, and the low pass filter The system is shown to have one input and seven functions with simple asymptotes and control is confined to operating at height to height from time to time Inputs to the command filter are developed along with decision rules, and two- and three-dimensional simulation algorithms are outlined M S K A82-39741 # Sensor stabilisation requirements of RPVs - A simula- tion study. K G Narayanan, M Madhuranath, S K Bhat, and G Elangovan (Aeronautical Development Establishment, Bangalore, India) In Remotely pi- loted vehicles, International Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 21 1-21 8 6 refs The application of pilot simulator video displays to the development of sensors for the stabilization of TV carrying RPVs is described • Either films with servo- induced roll, yaw, and jitter or numerically generated images can be displayed to the RPV TV sensor Particular attention is given to scaled geometric presenta- tions which produce out-the-window views to pilots Requirements for the simula- tion include accurate representations of objects, reflectance/radiance and contrast, RPV sensor accounting for resolution, sensitivity, FOV, look angle, slewing rate, image smear/lag, platform speed, direction, altitude, attitude, and maneuvers The data link is limited by the range of operation, bandwidth, and noise, and terrains are chosen for the approprate missio" Block diagrams are provided of the RPV sensor simulator and improvements necessary for the sys- tem to be operational M S K wave, millimeter wave, and laser radars for target detection and ranging The necessity of developing laser radars which operate at eyesafe wavelengths, such as 10 micron CO2 lasers, which are currently too heavy for UMA, is noted Data gathered by a UMA radar system is gained by means of a transmitter and a receiver, then relayed along a ground link Millimeter wave radars permit the use of 20 cm antennas on UMAs while maintaining an image resolution of 25 m at 1 5 km, operating at 100 GHz Flat plate printed circuit antennas several millimeters thick have been fabricated, permitting placement of the receiver on the same substrate as the antenna Employing magnetrons for high power gam is outlined M S K A82-39744 # Electric propulsion for a mini RPV system. G R See- mann and G L Harris (Developmental Sciences, Inc , City of Industry, CA) In Remotely piloted vehicles, International Conference, 2nd, Bristol, England, April 6-8, 1981, Supplementary Papers (A82-39727 19-01) Bristol, England, Univer- sity of Bristol, 1982, p 121-126 Contract No F33657-79-C-0508 ' The advantages of electric propulsion, such as reliable instant-start, enhanced survivacility, possible higher performance and improved storability, have merited further investigation Advances in the development of the lithium battery have increased the payload performance to 200-300 Wh/lb with the battery being the prime factor of the propulsion system concept A point design system of the mmi-RPV is described based on predictions after a strawman mission, and stud- ies of current and advanced concepts of an electric propulsion system are dis- cussed in terms of the components of the system Temperature control is studied, and performance estimates of the mmi-RPV are outlined such as a speed range of 60-150 kts, a climb rate of 600 ft/mm and an endurance of five hours The system's potential use as an expendable vehicle to conduct surveillance, jam- ming or kamikaze missions is foreseen R K R A82-39745 # Flight control systems for aerial targets. A W Bargery and K W Rosenberg (Marconi Avionics, Ltd , Rochester, England) In Remotely piloted vehicles, International Conference, 2nd, Bristol, England, April 6-8,1981, Supplementary Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 17 1-17 18 Research supported by the Ministry of Defence (Procure- ment Executive) Aerial targets, a class of unmanned aircraft (UMA), present constraints dif- ferent from other classes of UMA The control system design is partially deter- mined by data link, tracking facilities, and range location The flight control systems of two targets, the Jmdivik, in operation for 25 years, and the Sea Vixen, soon to be in operation, are described The Advanced Subsonic Aerial Target (ASAT) flight control system is under development, and its design approach, which anticipates a more expendable target vehicle, is described The ground station for the ASAT requires a high initial investment, but the air vehicle requires a minimal cost A comparison of each of these three systems is presented The Jmdivik has high operating skills, the Sea Vixen has medium skills, and the ASAT has low skills, while the Jmdivik and the Sea Vixen require large crews and the ASAT requires a small crew Block diagrams of each UMA are included R K R A82-39746 The design of a viewing system for near real time stereo images from a UMA borne linescan sensor J A C Beattie (Royal Aircraft Establishment, Farnborough, Hants, England) In Remotely piloted vehicles, International Conference, 2nd, Bristol, England, April 6-8, 1981, Supplementary Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 201-203 Laboratory trials demonstrate a display of stereoscopic images, received in data streams with a bandwidth of 512 kHz (-3 dB) The sensing and presentation of the data are described An optical system consisting of a German television lens of 10 2 mm focal length and an F number of 1 8 is used The image plane is divided in two by a right angle splitting prism with each half falling on a separate linear array angled 7 5 degrees from the optical axis The two linear arrays provide data alternately, which is converted to form a pair of visible images The demultiplexing system is explained, as well as various methods of storing the data The effect of cardboardmg is less severe with this system as it has an effective back drop The viewing system is described with its main problem being that a 90 degree twist in the image path is necessary for correct viewing The proposed air vehicle BAe (Filton) Stabileye Mkll is discussed In addition, it is shown that excessive movement may cause severe blurring, leading to difficulties in the fusion of the stereo pairs Fifty lines of horizontal disparity and 12 lines of vertical disparity can be tolerated with a good stereo viewing facility Two 4-bit images have been successfully stored and extracted using look up table meth- ods RKR A82-39742 # Radars for UMA. M Scorer ^viarconi Avionics, Ltd , Re- search Laboratory, Rochester, Kent, England) In Remotely piloted vehicles, International Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Pa- pers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 22 1 -22 6 The implementation of lightweight radar systems in unmanned aircraft (UMA) is discussed Attention is given to the application of UMA to air defense as a passive receiver system, carrying radiometers as a passive detector, and micro- A82-39747 # Opto-electromcal push-broom scanners for navigation, reconnaissance and generation of digital data bases. O Hofmann and P M W Nave (Messerschmitt-Bolkow-Blohm GmbH, Munich, West Germany) In Remotely piloted vehicles, International Conference, 2nd, Bris'ol, England, April 6-8, 1981, Supplementary Papers (A82-39727 19-01) Bristol, England, Univer- sity Of Bristol, 1982, p 20A 1-20A 3 494 A82-39896 A82-39750 # The design of a RPV ground station simulator. J Ford and P G Thomasson (Cranfield Institute of Technology, Cranfield, Beds ,.En- gland) In Remotely piloted vehicles, International Conference, 2nd, Bristol, En- gland, April 6-8, 1981, Supplementary Papers (A82-39727 19-01) Bristol, England, University of Bristol, 1982, p 26 1-267 Research supported by the Ministry of Defence (Procurement Executive) A simulator complex has been designed representing the ground station envi- ronment of a remotely piloted vehicle (RPV) system, in order to evaluate the human factors of a ground control station such as the work load of the crew The design requirements of the simulator are described, and the reasons for using a multicomputer design are explained The primary requirement of the simulator is that it operate in real time, and a second requirement is that it be flexible in order to accommodate specification changes in the system An example of the flexibility of the system is that the memory requirement of the system has increased from 24 K bytes to 128 K bytes with no need to modify the framework or computing capacity The goals in creating a ground control station are that it be able to preplan missions for the RPV, to control and replan missions while the RPV is airborne, and to interpret real time imagery Various diagrams are included R K R A82-39892 Evaluation of CFRP prototype structures for aircraft. Y Nontake, T Kohda, Y Abe, F Yamauchi, S Toyohira, K Mogami, H Arai, and N Arata (Japan Defense Agency, Technical Research and Development Insti- tute, Tachikawa, Tokyo, Japan) In Composite materials Mechanics, mechanical properties and fabrication, Proceedings of the Japan-U S Conference, Tokyo, Japan, January 12-14, 1981 (A82-39851 19-39) Barking, Essex, England, Ap- plied Science Publishers, 1982, p 478-486 The results of flight test programs to test the suitability of CFRP advanced composites for aircraft structures are presented The CFRP components tested included a rudder and rear nose landing gear door of a supersonic trainer, ground spoilers of a C-1 transport, and the outer leading edge slat rails of an antisubma- rine patrol seaboat Proof load tests were performed on the ground to affirm that the CFRP parts were as strong as conventional materials The flight tests covered stresses from velocity, altitude, angle of attack, and load factor of the aircraft and stress on the composite components Two and one-half years of flight data, with inspections every 200 hours and 9 months, were combined with com tapping tests for external structural elements No rigidity degradations were observed on the spoilers or the slat rails and all test components were evaluated as remaining in satisfactory condition M S K A82-39836 # Aerodynamic aspects of aircraft dynamics at high an- gles of attack /AGARD Lecture/. K J Orlik-Ruckemann (National Aeronauti- cal Establishment, Ottawa, Canada) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11. 1982, Paper 82-1363 22 p 37 refs This paper presents a review of some of the fluid dynamics phenomena that are associated with the oscillatory flight at high angles of attack, with particular emphasis on asymmetric shedding of forebody vortices, asymmetric breakdown of leading edge vortices, the oscillatory motion of such vortices, and the time lag between the motion of the vortices and that of the aircraft These phenomena cause a number of important effects on the dynamic stability parameters at high angles of attack (high alpha), such as strong nonlmeanties with alpha, significant, static and dynamic aerodynamic cross-coupling, large time-dependent and hys- teresis effects, and a strong configuration dependence The need to consider all the aerodynamic reactions in their vectonal form is emphasized, and the impor- tance of the abovementioned effects on our prediction capabilities of aircraft behavior at high alpha is discussed Development of adequate mathematical models is advocated and requirements for advanced wind tunnel techniques for performing the necessary oscillatory experiments are described The oral presentation is illustrated by movie films showing flow visualization on oscillating models (Author) A82-39882 On the state of technology and trends in composite materials in the United States. J R Vmson (Delaware, University, Newark, DE) In Composite materials Mechanics, mechanical properties and fabrication. Proceedings of the Japan-U S Conference, Tokyo, Japan, January 12-14,1981 (A82-39851 19-39) Barking, Essex, England, Applied Science Publishers, 1982, p 353-361 16 refs In connection with the ongoing NASA Aircraft Energy Efficiency Composite Primary Aircraft Program a number of composite material structural components have been installed on commercial aircraft and are in service today The compos- ite components involved include rudder, vertical fin, ailerons, elevators, and hori- zontal tail Attention is given to the use of graphite composites in commercial and military aircraft, F100 afterburner nozzle flaps made of carbon-polyimide com- posite, the graphite-epoxy airframe of the Learfan 2100, the use of Kevlar in helicopters, the employment of Kevlar composites in sailplanes, the fabrication of the fifty foot long booms of the Space Shuttle from graphite epoxy, and the use of Kevlar-epoxy in the design of many rocket motor cases Unfortunately, cost and confidence are still major obstacles toward more use of composites in the auto industry , G R A82-39890 Tests of CFRP spar/rib models with corrugated web. Y Tada, T Ishikawa, and E Nakai (National Aerospace Laboratory, Chofu, Tokyo, Japan) In Composite materials Mechanics, mechanical properties and fabrica- tion, Proceedings of the Japan-U S Conference, Tokyo, Japan, January 12-14, 1981 (A82-39851 19-39) Barking, Essex, England, Applied Science Publishers, 1982, p 461-470 5 refs Static strength tests are conducted on cantilever beams with corrugated web, models of spars and ribs used in aircraft structures, which are fabricated from carbon fiber reinforced plastics The shear strength of the corrugated web, the strain distributions, and the failure modes are evaluated for three types of models having different corrugation depths and laminate constructions Results show that the ultimate strengths of the webs are approximately equivalent to the shear strength of flat specimens of the same laminate construction In addition, the depth of the corrugation does not crucially change the strain distribution and the static bending strengths, but does effect the failure mode Strengthened layers of the flange-web connections have little effect on the web strength The critical - state of the webs can be identified by observing the magnitude of the surface strains, not by the displacements . N B A82-39893 Developments on graphite/epoxy T-2 nose landing gear door. K Mogami, F Yamauchi (Japan Defense Agency, Technical Re- search and Development Institute, Tachikawa, Tokyo, Japan), Y Sakatani, and Y Yamaguchi (Mitsubishi Heavy Industries, Ltd , Nagoya Aircraft Works, Nagoya, Japan) In Composite materials Mechanics, mechanical properties and fabrica- tion, Proceedings of the Japan-U S Conference, Tokyo, Japan, January 12-14, 1981 (A82-39851 19-39) Barking, Essex, England, Applied Science Publishers, 1982, p 487-493 Attention is given to the material systems and processing specially developed for the graphite/epoxy composite door, among them unidirectional tapes, fabrics, chopped fiber materials, and semi-cocurmg techniques To evaluate the durability of the graphite/epoxy skin laminates, water absorption tests and fatigue tests are performed at low, high, and room temperatures for the design required The all-graphite/epoxy beam-fittings were fabncated using the hot-pressing tech- nique and tested to verify the bearing and bending strength according to design requirements The saving in weight came to 25% C R A82-39894 Design, fabrication and qualification of the T-2 compos- ite rudder. F Yamauchi, K Mogami (Japan Defense Agency, Technical Re- search and Development Institute, Tachikawa, Tokyo, Japan), T Fukui, and T Sato (Fuji Heavy Industries, Ltd , Aircraft Engineering Div , Utsunomiya, Tochigi, Japan) In Composite materials Mechanics, mechanical properties and fabrica- tion, Proceedings of the Japan-U S Conference, Tokyo, Japan, January 12-14, 1981 (A82-39851 19-39) Barking, Essex, England, Applied Science Publishers, 1982, p 494-503 It is pointed out that this is the first primary control surface to be flight tested in Japan The rudder has a span of 1 53 m, a 0 71 -m chord at the midspan, and an area of 1 05 sq m The design involves a single-spar, full depth honeycomb sandwich structure Graphite/epoxy is used for the skins, spar, upper and lower closure ribs, and leading edge ribs The graphite/epoxy parts make up approxi- mately 40% of the total weight The spar and closure ribs are procured and bonded to the sandwich assembly after the skins are cured Nine procured leading edge ribs are attached with cherry-lock fasteners in addition to normal adhesive bonding It is noted that a conservative design approach was used and that the primary objectives were to obtain actual production experience and in-service operational experience for a composite primary control surface CR A82-39895 Development of the advanced composite ground spoiler for C-1 medium transport aircraft. F Yamauchi, K Mogami (Japan Defense Agency, Technical Research and Development Institute, Tachikawa, Tokyo, Japan), H Masaeda, and T Shirata (Kawasaki Heavy Industries, Ltd , Aircraft Div , Kagamihara, Gifu, Japan) In Composite materials Mechanics, me- chanical properties and fabrication, Proceedings of the Japan-U S Conference, Tokyo, Japan, January 12-14,1981 (A82-39851 19-39) Barking, Essex, England, Applied Science Publishers, 1982, p 504-512 The research and development program for the graphite/epoxy ground spoiler for the C-1 medium transport aircraft is discussed The design requirement was that the spoiler provide strength and rigidity not less than the baseline spoiler in addition to interchangeably The design analysis was done by finite element method and the detail design configurations of major structural components were evaluated by trade-off tests in the initial design phase, showing that the compo- nents met design requirements Successful environmental characteristic tests were also conducted The scattering characteristic of the Gr/E for static and fatigue strength were obtained and found to be significantly superior to that of aluminum alloy Full scale verification tests were also passed C D A82-39896 Fabrication of CFRP prototype structure for aircraft horizontal tall leading edge slat rail F Yamauchi, K Mogami (Japan Defense Agency, Technical Research and Development Institute, Tochikawa, Tokyo, Ja- pan), K Suzuki, T Kiho, and. T Ikuyama (Shin Meiwa Industry Co , Ltd , Kobe, 495 A82-39897 Japan) In Composite materials Mechanics, mechanical properties and fabrica- tion, Proceedings of the Japan-U S Conference, Tokyo, Japan, January 12-14, 1981 (A82-39851 19-39) Barking, Essex, England, Applied Science Publishers, 1982, p 513-520 Results of a fabrication study and materials properties tests of an advanced composite horizontal tail leading edge slat rail for the Japanese PS-1 STOL antisubmarine warfare seaplane are presented The slat rail was fabricated of carbon fiber satin cloth and a bisphenolic epoxy resin matrix, with co-curing by vacuum injection Static tests were performed to 100 and 180% of the design load limit and satisfactory results were obtained Coating the slat rail with silicon grease resulted in good resistance to salt spray, although stiffness was reduced 5% after 24,000 cycles High and low temperature environmental tests produced no degradation in the material The composite slat rails had been flown for 1000 hr in flight tests by 1978 and performed to specification M S K A82-39897 Development status of a composite vertical stabilizer for a jet trainer. K Takagi and S Idei (Fuji Heavy Industries, Ltd, Aircraft Engineering Div , Utsunomiya, Tochigi, Japan) In Composite materials Mechan- ics, mechanical properties and fabrication, Proceedings of the Japan-U.S Con- ference, Tokyo, Japan, January 12-14,1981 (A82-39851 19-39) Barking, Essex, England, Applied Science Publishers, 1982, p 521-528 Progress in a program to develop a composite materials vertical stabilizer for the next generation Japanese transonic military jet trainer is described Focusing on graphite/epoxy materials, the tests to date cover small elements, compo- nents, and full scale mam box trials The stabilizer is about 24m long with an area of 1 0 sq m, containing a two-spar multirib structure All component parts are graphite/epoxy except the ribs and root fittings, which are aluminum Tests have been run to examine the moisture temperature effects, rigidity, strain, and static loading to failure Results have indicated no inherent difficulty in accepting a composite stabilizer on the trainer M S K. A82-39929 Fasteners for composite structures. R T Cole, E J Bateh (Lockheed-Georgia, Co, Marietta, GA), and J Potter (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB, OH) (Symposium on Jointing in Fibre-Reinforced Plastics, London, England, July 13, 14, 1982) Composites, vol 13, July 1982, p 233-240 16 refs The four basic problems with fasteners for composites - galvanic corrosion, galling, installation damage, and low pull-through strength - are identified Seven special fastener systems for use in composites - bigfoots, semi-tubular rivets, Cherry Buck rivets, stress-wave rivet systems, groove proportioned lockbolts, composite fasteners, and self-tapping screws are described Survey results are shown indicating that flush, low-load transfer, composite-to-composite joints are the most common in current composite structures The rationale for selecting the flush head configuration as the modification considered is presented Test results indicate that 100 deg tension countersink fasteners are the best for sheet thick- nesses in excess of the head height (Author) A82-39930 On the bearing strengths of CFRP laminates. T A Coll- mgs (Royal Aircraft Establishment, Structures Dept, Farnborough, Hants, En- gland) (Symposium on Jointing in Fibre-Reinforced Plastics, London, England, July 13, 14, 1982) Composites, vol 13, July 1982, p 241-252 12 refs Bearing strength measurements have been made on zero, + and - 45, zero, 90 deg and 90 + and - 45 deg carbon fiber reinforced plastic (CFRP) laminates made from three different fibre/resin systems, HTS/914, XAS/914 and HTS/HC 3501 Equations have been derived for predicting the ultimate bearing strengths of constrained pin-loaded holes using a semiempincal approach, and considering the physical conditions governing failure at the hole edge Experimental results are presented and these show good agreement with those predicted for each of the laminate configurations and fibre/resin systems used (Author) A82-39996 t Numerical solution of a problem concerning transonic flow past a wing-fuselage configuration (Chislennoe reshenie zadachi ob okolozvukovom obtekanii kryla s fiuzeliazhem). V I Savitskn (Tsentral'nyi Aerogidrodmamicheskn Institut, Moscow, USSR) Gidromekhanika, no 46,1982, p 41-47 8 refs In Russian Nonviscous transonic flow past an arbitrary wing-fuselage configuration is analyzed within the framework of the small-perturbation theory A relaxation method is used in conjunction with a finite-difference scheme Finite-difference approximations for the relaxation equation and boundary conditions are selected by using nonstationary analogy To illustrate the method, calculations are earned out for several different wing-fuselage configurations V L A82-40051 Noise pollution and airport regulation. J L Helms (FAA, Washington, DC) Journal of Air Law and Commerce, vol 47, Spring 1982, p 405-412 Methods are proposed of reversing the trend of curfews and other limitations on airport use that have been adopted across the U S in the name of noise reduction or environmental protection The economic problems caused by airport restrictions are discussed along with the drawbacks of various types of restric- tions The situation in White Plains, New York is used as an example of the progress that can be made by holding litigation against restrictions in abeyance and cooperating with the FAA to bring about quick improvements An example of a beneficial rule is allowing the quietest planes to operate at night rather than banning night flights altogether, as was the case in White Plains The litigation route is briefly discussed, and the remedy of seeking systematic solutions is proposed, one combining legislation with FAA review C D A82-400S2 O'Hare International Airport - Impervious to proposed state efforts to limit airport noise. M J Pavlicek (Schaffenegger, Watson and Peterson, Ltd , Chicago, IL) Journal of Air Law and Commerce, vol 47, Spring 1982, p 413-448 199 refs The complexity of formulating a legally valid, technologically feasible, and economically reasonable state regulation that effectively abates noise at O'Hare International Airport is demonstrated The federal responsibility for airport noise, federal preemption and the role of the airport proprietor, and the Illinois Pollution Control Board's jurisdiction over the airport noise proposal before it is briefly discussed, while the proposal itself is dealt with in detail Particular attention is given to the variance procedure which mandates that the airport proprietor con- sider certain noise abatement methods which are under the control of another authority Noise abatement activities that can be directly implemented by the proprietor, those that require federal approval, and those that are controlled by local zoning authorities are discussed C D A82-40057 Touchdown technology. J Moxon Flight International, vol 122, July 24, 1982, p 215-217 The introduction of widebodied jets brought on a need for modifications in tires, brakes, and wheels to accommodate for weight Radial tires are being tested as they offer a 15-20% weight reduction Also, tires made of Guayule, a wild desert plant found in the southern United States and Mexico, are being tested The evolution of brakes is discussed, with the most recent development being the use of carbon disks as they absorb more kinetic energy than steel without overheat- ing Carbon also offers weight reduction and long life, but a more cost efficient production method is being investigated Variations in wheel production have been minimal and the current focus is on safety improvements and the use of titanium and aluminum alloys NASA is studying a new landing method which involves the active control of landing gear so that forces transmitted to the airframe are reduced R K R A82-40124 Two-dimensional model studies of the impact of aircraft exhaust emissions on tropospheric ozone. R G Derwent (Atomic Energy Research Establishment, Harwell, Oxon, England) Atmospheric Environment, vol 16.no 8. 1982, p 1997-2007 38 refs Research sponsored by the Depart- ment of Environment The potential effects of aircraft operations in the troposphere were investigated with a two-dimensional (latitude-altitude) transport-kinetics model There appears to be reasonable agreement between the present and previous studies that aircraft operations may have already increased ozone concentrations in the upper troposphere by up to a few per cent or so The corresponding increases in the total ozone column amount to a few tenths of a per cent and may well have partially offset any decrease due to the release of chlorofluorocarbons 11 and 12 (Author) A82-40276 # Flying quality requirements for V/STOL transition. C G Carpenter, J Hodgkmson (McDonnell Aircraft Co , St Louis, MO), R H Hoh (Systems Technology, Inc , Hawthorne, CA), and J W Clark, Jr (U S Naval Material Command, Naval Air Development Center, Warmmster. PA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Confer- ence, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1293 8 p 7 refs A landing approach criterion showed excellent correlation of heave damping and pitch-to-path coupling effects Blending schemes for transition from approach dynamics to hover dynamics, and vice versa, correlated well with earlier NASA results A time response criterion discriminated well between attitude and rate systems in low speed and hover Pilot's command gam has a strong effect on piloting charactersitics in all phases of transition (Author) A82-40287 # Flying qualities requirements for roll CAS systems. D G Mitchell and R H Hoh (Systems Technology, Inc , Hawthorne, CA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Confer- ence, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1356 9 p 8 refs Contract No. F33615-80-C-3604 Command augmentation systems (CAS) are becoming essential components for modern fighters A roll rate CAS utilizes an effective feedforward so that pilot control inputs are compared directly to actual roll response Such CASs. as they are used today, can be limited in authority with parallel direct links, or full- authority with high command gams The latter are the more interesting from a handling qualities standpoint Attention is given to gradient shaping, roll re- sponses for conventional aircraft, roll CAS gradients, roll ratcheting, implications for the handling qualities standard, roll performance, linearity, the roll mode time constant, and aspects of sensitivity G R 496 A82-40434 A82-40290 * # Flight-determined correction terms for angle of attack and sideslip. M F Shafer (NASA, Flight Research Center, Edwards, CA) American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechan- ics Conference. 9th. San Diego. CA, Aug 9-11, 1982, Paper 82-1374 11 p The effects of local flow, upwash. and sidewash on angle of attack and sideslip (measured with boom-mounted vanes) were determined for subsonic, transonic, and supersonic flight using a maximum likelihood estimator The correction terms accounting for these effects were determined using a series of maneuvers flown at a large number of flight conditions in both augmented and unaugmented control modes The correction terms provide improved angle-of-attack and sideslip val- ues for use in the estimation of stability and control derivatives In addition to detailing the procedure used to determine these correction terms, this paper discusses various effects, such as those related to Mach number, on the correc- tion terms The use of maneuvers flown in augmented and unaugmented control modes is also discussed (Author) A82-40294 * # The use of linearized-aerodynamlcs and vortex-flow methods in aircraft design /invited paper/. J E Lamar (NASA, Langley Research Center, Transonic Aerodynamics Div , Hampton, VA) American Insti- tute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference, 9th, San Diego. CA, Aug 9-11, 1982, Paper 82-1384 17 p 41 refs • This paper deals with selected lineanzed-aerodynamic and vortex-flow meth- ods as applied to aircraft design problems at high subsonic speeds In particular, the NASA Vortex Lattice and Modified Multhopp methods are the linearized techniques employed, and the suction analogy is used to provide estimates associated with vortex-flow aerodynamics Many examples are given as to how researchers at Langley have used these methods to design the high subsonic, wing-mean-camber shapes for various configurations such as a supersonic trans- port, high-aspect-ratio transport, trapezoidal fighter wing, strake wing, tandem wing, joined wing, delta wing, and slender cranked wing Many of these have been built, tested, and have had their data compared with theory In addition, a tech- nique for defining efficiently performing strake planforms for use in strake-wmg combinations is discussed, and further improvements in wing design are outlined The latter may be obtained by using higher-ordered linear panel methods as well as nonlinear-transonic methods (Author) A82-40348 Boeing's new 767 eases crew workload. R R Ropelew- ski Aviation Week and Space Technology, vol 117, Aug 23 1982, p 40 41 43 (3 ff) ' ' Details of the cockpit avionics and control switches and their operations in the Boeing 767 aircraft are described Automation of the control and monitoring of most aircraft functions has permitted elimination of the flight engineer's station, and all controls are now within reach of the pilot and copilot Each pilot is furnished electronic attitude director and horizontal situation indicators and flight manage- ment system control display units, in addition to sharing two centrally located 6 x 7 in electronic displays giving engine indication and crew alerts Standard electromechanical gages remain as a redundant feature, while checklist proce- dures are reduced to a short time Flight paths and travel times are currently being programmed for easy access loading into the flight computer for automated guidance, with the computer tuning to navigations aids stationed along the flight Path M S K A82-4039S # Summary of sting interference effects for cone, missile, and aircraft configurations as determined by dynamic and static measure- ments. B L Uselton and D R Haberman (Calspan Field Services, Inc , Arnold Air Force Station, TN) American Institute of Aeronautics and Astronautics, Atmo- spheric Flight Mechanics Conference, 9th, San Diego, CA, Aug 9-11, 1982, Paper 82-1366 16 p 21 refs A summary of an AEDC technology program of sting effects on aerodynamic measurements is presented Four different configurations - a 7-deg cone, 6-deg shced-base cone, missile and an aircraft - were tested in the wind tunnel Interfer- ence effects were obtained by measurements of damping derivatives, static data, surface pressures, and base pressures from subsonic to hypersonic Mach num- bers The critical sting limits were investigated as a function of frequency of oscillation, model boundary layer, type of measurement, angle of attack, Mach number, and configuration Comparisons of wind tunnel and ballistic range data are presented for the missile and aircraft configurations Critical sting length was found to be dependent on the parameter selected as the interference indicator (Author) A82-40417 * # NASA research in supersonic propulsion - A decade of progress. L H Fishbach, L E Stitt, J R Stone, and J B Whitlow, Jr (NASA, Lewis Research Center, Cleveland, OH) AIAA, SAE, and ASME, Joint Propul- sion Conference, 18th, Cleveland, OH, June 21-23, 1982, AIAA Paper 82-1048 23 p (Previously announced in STAR as N82-26300) A82-40418 * # Propulsion opportunities for future commuter aircraft. W C Strack (NASA, Lewis Research Center, Cleveland, OH) AIAA, SAE, and ASME, Joint Propulsion Conference, 18th, Cleveland, OH, June 21-23, 1982, AIAA Paper 82-1049 26 p 9 refs (Previously announced in STAR as N82-26298) A82-40419 * # Summary and recent results from the NASA advanced high-speed propeller research program. G A Mitchell and D C Mikkelson (NASA, Lewis Research Center, Cleveland, OH) AIAA, SAE, and ASME, Joint Propulsion Conference, 18th, Cleveland, OH, June 21-23, 1982, AIAA Paper 82-1119 34 p 37 refs (Previously announced in STAR as N82-26219) A82-40420 * # Performance of a 2D-CD nonaxisymmetric exhaust noz- zle on a turbojet engine at altitude. D M Straight and R R Cullom (NASA, Lewis Research Center, Cleveland, OH) AIAA, SAE, and ASME, Joint Propul- sion Conference, 18th, Cleveland, OH, June 21-23, 1982, AIAA Paper 82-1137 27 p 14 refs (Previously announced in STAR as N82-26241) A82-40422 * # Comparison of experimental and analytic performance for contoured endwall stators. R J Boyle (NASA, Lewis Research Center, Cleveland, OH) and J E Haas (U S Army, Propulsion Laboratory, Cleveland, OH) AIAA, SAE, and ASME, Joint Propulsion Conference, 18th, Cleveland, OH, Jung 21-23, 1982, AIAA Paper 82-1286 14 p 18 refs (Previously announced in STAR as N82-26299) A82-40428 # Terrain following/terrain avoidance system concept development. G D Young, Jr, W W Harrington, R L Overdorf, and E Ra- chovitsky (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB, OH) American Institute of Aeronautics and Astronautics, Guidance and Control Con- ference, San Diego, CA, Aug 9-11, 1982, Paper 82-1518 8 p 6 refs Grant No F33615-80-C-3617 The development of a real-time simulation of a terrain following/terrain avoid- ance (TF/TA) system algorithm for use with an operating AFTI/F-16 simulator is described The simulator is equippped with a control feel system, a single seat cockpit, an earth/sky and a target/terrain projection system, and motion and g-force provisions A 5000 1 scale scenario of western Europe was chosen with night, dusk, and daylight capability in addition to'cloud cover and weather configu- rations The TF/TA control system is considered in terms of a preplanned ground track, with the mission proceeding from waypomt to waypomt, a computed flight path, for optimized aircraft performance on trajectories within the mission path, and aircraft control to follow the actual flight path A feasible directions algorithm for obtaining the computed flight path is presented and operations are described Further developments to complete the pilot-m-the loop strategies are discussed MSK A82-40429 * # Right experience with a backup flight-control system for the HIM AT research vehicle. R W Kempel (NASA, Flight Research Center, Edwards, CA) American Institute of Aeronautics and Astronautics, Guidance and Control Conference, San Diego, CA, Aug 9-11, 1982, Paper 82-1541 20 p The NASA Dryden Flight Research Facility is conducting flight tests of two remotely piloted, subscale, advanced fighter configurations, the tests are part of the Highly Maneuverable Aircraft Technology (HiMAT) project Closed-loop pri- mary flight control is performed from a ground-based cockpit and digital com- puter in conjunction with an up/down telemetry link A significant feature of these vehicles is an on-board, digitally active, backup control system designed to recover the vehicle in the event of a transfer from primary control Automatic transfers occur upon certain critical ground or airborne system malfunctions Control modes are provided that enable a ground or airborne controller to guide the vehicle to a safe landing This paper describes the features, operational development, and flight evaluation of the HiMAT backup flight control system (Author) A82-40434 # Analytical design and validation of digital flight control system structure. D B Mulcare, W G Ness, and R M Davis (Lockheed- Georgia Co , Marietta, GA) American Institute of Aeronautics and Astronautics, Guidance and Control Conference, San Diego, CA, Aug 9-11. 1982, Paper 82-1626 11 p 17 refs Flight controls applications continue to be a dominant driver of applied digital technology, especially in the areas of fault-tolerant computer subsystems and flight-critical assurance methods The present investigation is concerned with two of the major digital flight system technology needs, taking into account system validation technology and integrated methodology Attention is given to the inte- gration of assurance activities or provisions into the design process The problem at hand is to formulate, develop, and validate an analytically based methodology which can dependably yield a readily validatable and maintainable digital flight control system Questions of basic strategy are considered along with the techni- cal approach, the control of complexity, a design description, aspects of system validation, and questions of development methodology G R 497 A82-40483 A82-40483 t Sport aircraft (Sportivnye samolety). S A lakovlev Mos- cow, Izdatel'stvo DOSAAF SSSR, 1981 72 p In Russian The development and character of sport aviation in the Soviet Union are dis- cussed, with attention given to the historical background and the line of Yak light aircraft Non-Soviet sport aircraft are also considered Many color drawings of sport aircraft are presented B J A82-4050S American Helicopter Spciety, Annual Forum, 38th, Ana- heim, CA, May 4-7, 1982, Proceedings. Washington, DC, American Helicopter Society, 1982 537 p (For individual items see A82-40506 to A82-40556) Among the topics discussed are the aerodynamics, structural dynamics, pro- pulsion, design, avionics, product assurance, structures and materials, testing, and acoustics of helicopters The papers presented cover optimum airloads of rotors in hover and forward flight, the evaluation of vertical drag and ground effect, helicopter vibration reduction by rotor blade modal shaping, the finite element analysis of beanngless rotor blade aeroelasticity, adaptive fuel controls, digital full authority engine controls, helicopter autorotation assist concepts, and the conceptual design of an integrated cockpit Also presented are papers on the demonstration of radar reflector detection, avionics systems for helicopter inte- gration, the adaptation of pultrusion to the manufacture of helicopter components, composite main rotor blades, optimum structural design, the in-plane shear test- ing of thin panels, error minimization in ground vibration testing, and the prediction of helicopter rotor discrete frequency noise O C A82-40506 # Theory and application of optimum airloads to rotors in hover and forward flight. R C Moffitt and J R Bissell (United Technologies Corp, Sikorsky Aircraft Div , Stratford, CT) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 1-12 (For in- dividual items see A82-40506 to A82-40556) A method is derived and applied that predicts optimum lift distribution for rotors in hover and forward flight A key feature of the method is that it is formulated in terms of a matrix equation that gives a direct solution when wake geometry is fixed An evaluation of the Theodorsen optimum static propeller theory, con- ducted with the analysis, indicates that the theory is not rigorous It is shown that the torque differential term omitted in that analysis is both finite and significant With this term included, the optimum static propeller wake displacement velocity is not constant An optimized Black Hawk twist distribution in hover is shown to closely approximate the classic inverse radius pitch distribution predicted by strip momentum theory The resulting downwash, however, is constant only over the inner 75% of the radius and substantial reductions occur in the tip region Pre- dicted improvements in Black Hawk forward flight performance with optimized azimuthally varying twist are significant but the associated variable twist is com- plex (Author) A82-40507 # A new Transonic Airfoil Design Method and its applica- tion to helicopter rotor airfoil design. J C Harramore and J G Yen (Bell Helicopter Textron, Fort Worth, TX) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 13-23 28 refs A new Transonic Airfoil Design Method has recently been developed which can produce airfoils with desired aerodynamic, dynamic, and geometric characteris- tics This new method is based on fundamental principles and utilizes efficient techniques to provide a practical airfoil design tool Compressibility and shock wave terms are included in the method which evaluates families of velocity distributions and selects the best one which will satisfy the design objectives This pressure distribution is used as input to a transonic inverse routine which calcu- lates the coordinates of the section that will produce the desired velocity Using this approach, sections can be produced that will provide desired levels of lift, drag, and pitching moment at the design operating conditions This technology is applied to the design of an aeroelastically compliant rotor (ACR) by designing airfoils which produce favorable pitching moment and performance at design Mach number and Reynolds number conditions (Author) A82-40508 # Recent advances in rotor technology at Boeing Vertol. M A McVeigh and F J McHugh (Boeing Vertol Co , Philadelphia, PA) In Ameri- can Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Pro- ceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 24-33 Results of a wind tunnel test on advanced rotor configurations present an assessment of the benefits of advanced airfoils, tip shape, blade chord, and blade number A CH-47D model rotor with VR-7/8 airfoils was tested as a reference rotor The advanced rotors, incorporating recently-developed VR-12/15 high speed airfoils, were tested to 231 knots in the wind tunnel and demonstrated an improvement of 6 0% in figure of merit and 25% in cruise lift-to-effective-drag ratio over a rotor with VR-7/8 airfoils The advanced airfoils show significant improvements in stall inception limits, flying qualities boundaries and rotor noise Improved blade tip shapes provide additional benefits in rotor noise and do not reduce the stall inception boundary (Author) A82-40509 * # Evaluation of an asymptotic method for helicopter rotor airloads. A R Vaidyanathan and G A Pierce (Georgia Institute of Technology, Atlanta, GA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 34-42 21 refs Contracts No NAS1-16222, No NAS1-16817 (Previously announced in STAR as N82-21156) A82-40510 * -# An evaluation of vertical drag and ground effect using the RSRA rotor balance system. R J Flemmmg (United Technologies Corp, Sikorsky Aircraft Div , Stratford, CT) and R E Enckson (NASA, Ames Research Center, Moffett Field, CA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 43-54 12 refs A flight test program utilizing the Rotor Systems Research Aircraft (RSRA) mam rotor balance system was conducted to obtain data for the helicopter configuration The test program is discussed along with the employed data reduc- tion methods, and the results NASA 740, the RSRA used for the vertical drag test, was in the standard helicopter configuration The 31 -foot radius blades have a linear twist of eight degrees and NACA 0012 airfoil sections Aspects of in- strumentation are considered, taking into account the data recording system, the static calibration facility, and aspects of data calibration and processing Attention is given to the test procedure, data analysis methods, balance measurements, the ground effect, and vertical drag It is found that the RSRA rotor balance system is capable of providing high quality performance data The vertical drag of the RSRA is 4%, compared to 2 9% predicted G R A82-40511 * # Effect of tip vanes on the performance and flow field of a rotor In hover. H R Velkoff and T W Parker (Ohio State University, Colum- bus, OH) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982. Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 55-64 7 refs NASA-sponsored research Tests run with a single bladed model rotor with a vane located at the tip of the blade indicated significantly increased performance under certain test conditions Data reveal that a figure of merit increase of over one third occurred in hover Flow visualization using smoke revealed that a pair of vortices sprung from the blade tip and the vane tip The vane tip vortex tended to roll up and over the primary vortex The vortices in the wake became much less well defined with the tip vane configurations (Author) A82-40512 # An experimental investigation of a beanngless model rotor in hover. S Dawson (U S Army, Aeromechanics Laboratory, Moffett Field, CA) In American Helicopter Society, Annual Forum. 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Heli- copter Society, 1982, p 65-79 6 refs A 1 79-m diameter model rotor was used to investigate the aeroelastic stability of an isolated beanngless rotor blade in hover, and the results were compared with theory Configurations tested included (1) an uncoupled configuration with a leading and trailing edge pitch link, (2) a cantilever pitch arm configuration with a single pitch link on the trailing edge of the blade (three pitch link radial locations were studied), (3) a cantilever pitch arm configuration with a single trailing edge pitch link (again three radial locations were studied), (4) a trailing edge pitch link location with -2 5 deg droop, and (5) a trailing edge pitch link location with 2 5 deg precone Lead-lag damping was heavily dependent on pitch link radial location at higher pitch angles for the cantilever pitch arm configurations studied Theoreti- cal predictions show stability trends quite well in almost all cases but show discernible differences in damping at higher pitch angles (Author) A82-40513 # Whirl mode stability of the main rotor of the YAH-64 Advanced Attack Helicopter. L J Silverthorn (Hughes Helicopters, Inc , Culver City, CA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 80-89 The selection of the main rotor configuration for the YAH-64 helicopter was based on the very favorable experience with the combat-proven rotor system of the OH-6A Light Observation Helicopter Results of an analysis conducted to investigate the main rotor cyclic modes have shown an instability at the advancing whirl mode frequency of 15 hertz The whirl mode instability was eliminated in connection with design changes It is pointed out that the whirl mode instability is an aeroelastic phenomenon strongly dependent on coupling between hub motion and blade pitch change motion Rotor support structure stiffening proved to be effective in increasing whirl model stability boundaries G R A82-40514 # Helicopter vibration reduction by rotor blade modal shaping. R B Taylor (United Technologies Research Center, East Hartford, CT) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA. May 4-7, 1982. Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 90-101 498 A82-40523 The general vibration design criteria currently used in helicopter rotor blade design is placement of natural frequencies removed from integer frequencies of rotor rotation In this paper, a theoretical approach is presented which demon- strates that design consideration of blade mode shapes can be as important as consideration of natural frequencies for vibration transmitted to the helicopter fuselage A Modal Shaping Parameter is derived from the theoretical approach that is a measure of blade modal vibration susceptibility A baseline blade design is then revised m accordance with minimizing the value of the Modal Shaping Parameter A comparison of hub vibration predicted by a fully coupled aeroelastic analysis for the baseline and revised blade design shows a 70 percent reduction in the contribution of the flatwise modes to vertical hub vibration as well as a 20-30 percent reduction in blade fatigue loading It is demonstrated that the large reductions in vibration resulted directly from desensitizing certain blade modes to aerodynamic loading as predicted by the modal shaping approach (Author) A82-40S1S # Correlation of predicted vibrations and test data for a wind tunnel helicopter model. R Sopher and S B R Kottapalli (United Tech- nologies Corp , Sikorsky Aircraft Div , Stratford, CT) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82- 40505 20-01) Washington, DC, American Helicopter Society, 1982, p 102-113 9 refs The desirability to reduce helicopter vibrations has motivated the development of a substructure vibration analysis The computer program involved is designed to serve as a predictive and design tool for designing helicopters for low vibra- tions The substructure analysis, (SIMVIB - Simplified Vibration Analysis) embo- dies features which are necessary for vibration prediction Little is known about the validity and sensitivity of the conducted analysis A description is presented of the results of a limited correlation study performed at model scale to examine the method The correlations of fuselage vibrations and blade moments are presented and discussed Sensitivities of analytical predictions to changes in dynamic properties of the fuselage are shown In addition, a study is conducted of the correlation of analysis and theory when higher harmonic control is applied to the rotor to minimize fuselage vibrations G R A82-40516 # Wind tunnel modeling of rotor vibratory loads. R Gabel, M Sheffler, F Tarzamn, and D Hodder (Boeing Vertol Co , Philadelphia, PA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982. p 114-124 A tandem rotor dynamic model has been designed, manufactured and tested at the Boeing Vertol 20 x 20 ft V/STOL Wind Tunnel The model measures vibratory hub loads with five independent measuring systems on each rotor This four-bladed model was flown at full scale tip speeds through a wide envelope of airspeeds and thrusts, achieving a maximum speed of 200 knots The various measurement systems are discussed, calibration activities are reviewed and test results are presented (Author) A82-40517 * # Finite element analysis for bearingless rotor blade aeroelasticity. N T Sivanen and I Chopra (NASA, Stanford Joint Institute for Aeronautics and Acoustics, Stanford, CA) In American Helicopter Society, An- nual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 125-139 18 refs Grant No NCC2-13 A conventional articulated rotor blade has mechanical flap and lag hinges, a lag damper, and a pitch bearing In connection with an interest in designs of greater mechanical simplicity and increased maintainability, hmgeless and bear- ingless rotors have been developed A hmgeless blade lacks the hinges and is cantilevered at the hub It does have a pitch bearing for pitch control A bearing- less design eliminates the hinges and the pitch bearing as well In the present investigation of bearingless rotor blade characteristics, finite element analysis has been successfully applied to determine the solutions of the nonlinear trim equations and the linearized flutter equations of multiple-load-path blades The employed formulation is based on Hamilton's principle The spatial dependence of the equations of motion is discretized by dividing the flexbeams, the torque tube, and the outboard into a number of elements G R A82-40518 * # Civil helicopter propulsion system reliability and engine monitoring technology assessments. J A Murphy (Bell Helicopter Textron, Fort Worth, TX) and J Zuk (NASA, Ames Research Center, Moffett Field, CA) In American Helicopter Society. Annual Forum, 38th, Anaheim, CA, May 4-7, 1982. Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 140-149 16 refs NASA-supported research A study to reduce operating costs of helicopters, particularly directed at the maintenance of the propulsion subsystem, is presented The tasks of the study consisted of problem definition refinement, technology solutions, diagnostic sys- tem concepts, and emergency power augmentation Quantifiable benefits (re- duced fuel consumption, on-condition engine maintenance, extended drive system overhaul periods, and longer oil change intervals) would increase the initial cost by $43,000, but the benefit of $24 46 per hour would result in brea- keven at 1758 hours Other benefits not capable of being quantified but perhaps more important include improved aircraft avilability due to reduced maintenance time, potential for increased operating limits due to continuous automatic monitor- ing of gages, and less time and fuel required to make engine power checks The most important improvement is the on-condition maintenance program, which will require the development of algorithms, equipment, and procedures compatible with all operating environments R K R A82-40519 # Adaptive fuel control feasibility investigation. R L Bol- ton (U S Army, Applied Technology Laboratory, Fort Eustis, VA) In American Helicopter Society, Ann.ua! Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceed- ings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 150-155 Responsive, stable power control has been an important design objective since the advent of the helicopter Many helicopters flying today, however, suffer from less than desirable power response because of the difficulty in designing a sys- tem which is rapid in rotor speed control over the entire operating envelope An optimization regarding the response of engine power for all flight regimes would 'be particularly important in the case of a combat helicopter A description is presented of an on-going program of investigation of adaptive fuel control con- cepts utilizing existing full authority electronic systems capability The concepts developed in this program are being analyzed by use of a full dynamic computer simulation of the engine/fuel control/airframe It was found that fuel consumption can be reduced as much as 10% by variation of rotor speed for very specific cruise conditions, i e , high speed, high altitude, and heavy load G R A82-40520 # 800 Shaft Horsepower Advanced Technology Demon- strator Engine (ATDE) status update. D B Cale (U S Army, Applied Tech- nology Laboratory, Fort Eustis, VA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC,'American Helicopter Society, 1982, p 156-162 The objectives, engine design features, accomplishments and current status of the ATDE program are presented More than 1000 hours of engine and gas generator testing have been accumulated, including performance, environmental and durability testing, and objectives are being demonstrated and problems dis- covered More than 1500 hours of aerodynamic component testing and 4000 hours of fuel system and mechanical component testing have also been done In particular, the durability demonstration was considered successful, but certain redesign efforts, such as inlet separator performance and producibility, compres- sor durability, and bearing durability, are necessary and are being considered R K R A82-40521 * # TF34 Convertible Engine System Technology Program. K L Abdalla (NASA, Lewis Research Center, Cleveland, OH) and A Brooks (General Electric Co , Lynn, MA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 163-165 8 refs The ability of the helicopter to function efficiently at zero flight speed is counter- balanced by a limitation to rather low forward flight speeds An ability to fly efficiently at high speed would provide very significant improvements in rotorcraft productivity and economics The implementation of such improvements would require the development of a suitable integrated power plant for both the vertical and horizontal flight modes The engine should be a shaft output engine in the vertical flight mode In the horizontal mode, the propulsor can be fan or propeller A description is presented of a program concerned with the demonstration of a convertible turbofan/turboshaft engine The program is nominally directed toward the demonstration of a propulsion system for an X-wmg aircraft However, the principles being investigated are applicable to any convertible turbofan/turbo- shaft engine application At the current early stage of the program, no barrier problems have become apparent, and interesting possibilities for high speed rotorcraft flight are envisaged G R A82-40522 # Digital full authority controls for helicopter engines. E S Eccles (Dowty and Smiths lndustnasJ3ontrols, Ltd , Cheltenham, Glos , En- gland) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Heli- copter Society, 1982, p 170-180 5 refs Research supported by the Ministry of Defence /Procurement Executive/ The paper reviews the benefits that accrue to the aircraft, the operator and the crew from using full authority digital electronic engine controls They are dis- cussed as performance benefits, mission effectiveness benefits, cost benefits and maintainability benefits The paper discusses the use of redundancy and its effects on the operation of aircraft, particularly commercial operation The paper concludes that digital controls, and particularly dual redundant controls ofter some very significant cost benefits to many helicopter operators (Author) A82-40523 # Tandem rotor helicopter characteristics in a continuous icing environment. P J Dunford (Boeing Vertol Co , Philadelphia, PA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 181-193 9 refs 499 A82-40524 In connection with the growing need for Instrument Flight Rule (IFR) operations in both military and commercial applications, considerable emphasis has been placed on helicopter utilization in adverse weather conditions As a corollary to this requirement, investigations have been conducted with the aim to permit the operation of helicopters under icing conditions Attention is given to test results, a natural icing performance analysis, the need for a deicmg system, and icing certification criteria It is found that the impracticably and expense involved in testing helicopters to the full extent of the requirements of FAR Part 25 makes the need for LIMITED icing releases a real one Recognition of specific helicopter attributes and shortcomings is highly desirable for this type of, certification GR A82-40524 # An evaluation of helicopter autorotation assist con- cepts. G T White (U S Army, Applied Technology Laboratory, Fort Eustis. VA), A H Logan, and J D Graves (Hughes Helicopters. Inc, Culver City, CA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 194-216 11 refs Grant No DAAK51-80-C-0011 Tho unique autorotation capability of the helicopter is an inherent safety feature which is heavily relied upon during power failure emergencies However, the autorotation maneuver places great demands on pilot skill An analytical study was conducted of autorotation improvement devices These devices were evalu- ated using both weight and preliminary performance analyses The three most promising concepts were carried through preliminary design It was found that no significant gain in autorotation performance can be achieved by only the manage- ment of available baseline energy Supplemental energy must be supplied The use of a simple Autorotative Index is a good tool for the initial determination of the auxiliary power level required for good autorotative characteristics The au- torotative characteristics of a single-engine scout helicopter can be substantially improved with the combination of a MIL-STD-1290 type landing gear and either a Tip Jet, Flywheel or Auxiliary Turbine system " G R A82-40525 # Predeslgn study for an advanced flight research rotor. R H Blackwell, T G Campbell (United Technologies Corp , Sikorsky Aircraft Div , Stratford, CT), and R B Taylor (United Technologies Research Center, East Hartford. CT) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 217-234 11 refs A flight research rotor program aimed at demonstrating significant improve- ments in aerodynamic performance and reductions in vibration and noise is out- lmed_TheJ:enefits and practical design_cqnsiderations of approximately a dozen advanced rotor concepts were considered and three concepts were chosen for inclusion in the flight research program Detailed design of a blade permitting experimental study of tip shape, a tuned trailing edge tab system and blade mass distribution is presented The design issues addressed in connection with the research blade are shown to have general applicability Finally the total program required to develop these concepts including further analysis, model test, ground tests and flight test is outlined (Author) A82-40526 # Sikorsky ACAP preliminary design. B F Kay (United Technologies Corp, Sikorsky Aircraft Div., Stratford, CT). In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-4050520-01) Washington, DC, American Helicopter Society, 1982, p 235-238A Sikorsky Aircraft is currently under contract to the U S Army to conduct an Advanced Composite Airframe Program (ACAP) The basic objectives of the ACAP are to demonstrate the weight and cost saving potential of advanced composite materials when used to the maximum extent possible in an airframe designed to meet stringent military requirements This paper will describe Sikor- sky's ACAP helicopter and the approaches used to minimize weight, reduce manufacturing costs and achieve high levels of crashworthiness, survivabihty, reliability, and maintainability (Author) A82-40527 # Conceptual design of the LHX integrated cockpit R R Pruyn and R E Domenic (Boeing Vertol Co, Philadelphia, PA) In Amencan Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceed- ings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 239-246 9 refs The present investigation is concerned with the application of computer-based technology to the next generation of Army tactical aircraft Attention is given to missions which drive cockpit design, the potential benefits of improved displays, developments in automation, questions regarding the merits of displays versus windows, mockups to develop design, aspects of display capability and flight safety, concepts in image processing, crew workload studies, assumptions for workload analysis, workload methodology, and the results of workload analysis It is concluded that with the anticipated automation, controls, and displays, one crewman can efficiently perform all of the desired tactical scout and attack tasks For next-generation aircraft a wide-field-of-view panel or helmet-mounted display is needed since it reduces pilot workload and improves mission performance and flight safety G R A82-40528 # The YAH-64 empennage and tail rotor - A technical his- tory. R W Prouty and K B Amer (Hughes Helicopters. Inc . Culver City. CA) In American Helicopter Society, Annual Forum. 38th. Anaheim. CA. May 4-7. 1982, Proceedings (A82-40505 20-01) Washington, DC. American Helicopter Society, 1982. p 247-261 The development of a helicopter from drawing board to production line is still very much a learning process The lessons learned in connection with the devel- opment of the Army YAH-64 Advanced Attack Helicopter should, therefore, be sufficiently valuable to future designers to warrant a detailed review Attention is given to the changes to the empennage and tail rotor as the designers sought the best compromise between good performance and flying qualities on the one hand and low weight, low cost, and simplicity on the other The considered helicopter has been developed primarily as a tank hunter and killer capable of flying and fighting at night or in bad weather The primary weapons are wingmounted Hellfire guided missiles The work discussed primarily deals with solutions to problems in the basic aircraft as they were discovered during its flight test G R A82-40529 # Future helicopter cockpit design. S D Roy (Westland Helicopters, Ltd , Yeovil, Somerset. England) In American Helicopter Society. Annual Forum. 38th, Anaheim, CA. May 4-7, 1982, Proceedings (A82-40505 20-01) Washington. DC, American Helicopter Society. 1982. p 262-273 5 refs The influence of the use of electronic display systems on the helicopter cockpit is examined Color CRT's are decidedly essential when proposed as complete replacements for conventional instruments, and two sizes of display are being considered (5 inches x 5 inches and 8 inches x 8 inches) Lighter displays, using flat panel technology, should be considered for the long term, but with careful consideration of pilot error due to misselection Other technologies considered are data entry and extraction techniques, and direct voice control systems The data technique is considered in terms of class of task, access, time constraints, and space availability, and a design approach for a voice system capable of continuous speech recognition is presented The cockpit design implications of these modifications are considered R K R A82-40530 # Concept demonstration of automatic subsystem parameter monitoring. M S Randolph (General Electric Co , Aerospace Con- trol Systems Dept, Bmghamton, NY) and R V Kurowsky (U S Army. Fort Mon- mouth. NY) In American Helicopter Society, Annual Forum. 38th, Anaheim, CA. May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 274-286 Grant No DAAK80-79-C-0270 A feasibility demonstration model of an Electronic Master Monitor and Advisory Display System (EMMADS) has been developed as part of the Army's efforts to reduce aircrew workload, integrate cockpit instrumentation, and enhance aircraft maintenance capability The feasibility demonstration hardware is considered along with aspects of system operation, taking into account the philosophy of operation, the types of operation, manually commanded operations, and fault commanded operations Under a follow on development effort Currently in progress, the capabilities of the current feasibility hardware will be expanded to include fault logic for all CH-47D model subsystems G R A82-40531 * # Flight test evaluation of a video tracker for enhanced offshore airborne radar approach capability. G R Clary (NASA, Ames Re- search Center, Moffett Field, CA) and,P G Cooper (Cooper Avionics. Inc. Montara, CA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982. Proceedings (A82-40505 20-01) Washington. DC, American Helicopter Society, 1982. p 287-297 7 refs ,As a part of NASA's Rotorcraft All-Weather Operations Research Program, advanced airborne radar approach (ARA) concepts are being investigated Since data from previous NASA/FAA flight tests showed significant ARA limitations, a research program was initiated at NASA Ames Research Center to determine the benefit that could be derived by automating certain radar functions and superim- posing course display data on the radar display To evaluate these concepts, a newly developed video tracking system which interfaces with weather radar was acquired After the pilot designates a destination target, the system tracks the target video as it moves on the radar indicator Using a small, efficient micro- processor, the autotracker presents valuable approach data on the radar screen and automatically adjusts the radar gam and tilt Results of a limited flight test evaluation of the autotracker show that the course display concept, combined with automated gam and tilt functions, is effective for improving ARA's and reduc- ing radar operator workload (Author) A82-40532 * # Demonstration of radar reflector detection and ground clutter suppression using airborne weather and mapping radar. D J Ander- son, J S Bull (NASA, Ames Research Center, Moffett Field. CA), and J P Chisholm (Nevada, University, Reno. NV) In American Helicopter Society. An- nual Forum, 38th. Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 298-305 A navigation system which utilizes minimum ground-based equipment is espe- cially advantageous to helicopters, which can make off-airport landings Re- search has been conducted in the use of weather and mapping radar to detect large radar reflectors overland for navigation purposes As initial studies have not 500 A82-40542 been successful, investigations were conducted regarding a new concept for the detection of ground-based radar reflectors and eliminating ground clutter, using a device called an echo processor (EP) A description is presented of the prob- lems associated with detecting radar reflectors overland, taking into account the EP concept and the results of ground- and flight-test investigations The echo processor concept was successfully demonstrated in detecting radar reflectors overland in a high-clutter environment A radar reflector target size of 55 dBsm was found to be adequate for detection in an urban environment G R A82-40533 # Micro-heads-up display. J R Goodman and H W Upton (Bell Helicopter Textron, Fort Worth, TX) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 306-311 A revolutionary microsized heads-up display (micro-HUD), which weighs only a few ounces and can be worn as a pair of conventional eyeglasses, is described A microsize optical system makes the display possible An advanced state-of- the-art visible light-emitting diode (VLED) array and a vibrating fiber ribbon gener- ate the image The system uses a microprocessor display generator that produces a dynamic image with 128 x 128 elements of resolution This gives the micro-HUD the capability of presenting the same information as a standard heads-up display Development of the custom-designed linear array of light- emitting diodes along with the specially fabricated fiber-optic scanner is also described Results of laboratory and flight tests are discussed Potential improve- ments such as higher resolution and multicolor versions of the display are de- scribed Finally, the possible applications and future of the system is discussed (Author) A82-40534 # Avionics systems for helicopter integration. D R Nel- son (Rockwell International Corp , Collins Government Avionics Div , Cedar Rap- ids, IA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Heli- copter Society, 1982, p 312-321 Attention is given to a 'core system' which provides a common set of equip- ments that is, with appropriate software, applicable to a wide variety of helicopter missions The basic core system is the core of the Coast Guard {USCG) HH-65A system It has been proposed for civil and military helicopter programs with requirements ranging from covert 'behind-the-lmes' operations to resupply of oil rigs Particular elements of the core avionics systems include the Cockpit Man- agement System (CMS), the Multi-purpose Video Display System, the Mission Computer, a dual redundant multiplex data bus control system, and a four-axis autopilot/flight director capable of hands-off flight in all regimes including transition to hover Attention is given to system capability requirements, aspects of system functional allocation, the automatic flight control system, and the mis- sion processor G R A82-40535 * # NASA/FAA Helicopter ATC simulation investigation of RNAV/MLS Instrument approaches. L L Peach, Jr, L Tobias, and H Q Lee (NASA, Ames Research Center, Moffett Field, CA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82- 40505 20-01) Washington, DC, American Helicopter Society, 1982, p 322-336 6 rets The NASA/FAA Helicopter Air Traffic Control (ATC) simulation investigations to determine the feasibility of simultaneous, independent instrument approach procedures for helicopters at major terminal areas, using Area Navigation/Mi- crowave Landing System (RNAV/MLS) guidance, was conducted at several levels of helicopter display sophistication, up to that of a Cockpit Display of Traffic Information (CDTI) system Test objectives included the determination of pilot acceptability and the tracking performance of the RNAV/MLS's noninterfenng rotorcraft approach path structure, along with the evaluation of the effect on controller workload of multiroute structures combining conventional and rotor- craft approaches at various arrival rates and traffic separations The utility of electronic area maps and CDTI displays was also investigated Participating pilots flew 127 simulated instrument approaches in an ATC simulation laboratory OC A82-40537 # Adaptation of pultrusion to the manufacture of heli- copter components. E E Blake (Bell Helicopter Textron, Fort Worth, TX) and N J Tessier (U S Army, Army Materials and Mechanics Research Center, Wa- tertown, MA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 346-351 • • A fabrication technique is described in which pultruded epoxy/glass stock with a complex crossection is postformed and cured to produce a curved UH-1 heli- copter door track During pultrusion, prepreg roving is overwrapped with adhesive prepreg glass cloth for transverse strength The 'B' stage stock is postformed and autoclave cured in a glass/epoxy toot The resulting door track retains the cros- section of the pultrusion after developing the sweep and twist designed into the present aluminum part Wear and load testing were performed on the composite door track along with an economic analysis comparing it with hand layup and the present aluminum track The results demonstrate that it is feasible to produce complex helicopter components from pultrusions by means of postformmg (Author) A82-40538 # In-motion radiography of titanium spar tube welds. R J Milne (United Technologies Corp , Sikorsky Aircraft Div , Stratford, CT) In Ameri- can Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Pro- ceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 352-358 The application of titanium to a helicopter rotor blade spar was developed during the 1960's However, the initially contemplated manfacturmg method did not prove to be economical, and a new manufacturing procedure involving the use of a plasma arc welding technique was developed The verification of weld integ- rity by means of a typical static X-ray test was found to be too time consuming, and the employment of m-motion radiography was considered By using an m- motion radiographic system, it was possible to reduce significantly the time re- quired to radiograph spar tube welds without sacrificing detail sensitivity G R A82-40539 # Development of the Sea King composite main rotor blade. R Sanders (Westland Helicopters, Ltd , Yeovil, Somerset, England) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 359-370 The Sea King composite mam rotor blade has been designed to satisfy rugged- ness requirements for the 1980's, and will soon be ready for flight testing Com- posite materials with a replacable metal erosion shield have been chosen to improve the life of the blade, and a carbon and glass fiber mixture satisfies stiffness and weight requirements A bolted root end design was chosen for this retrofit blade in order to-ease automation, without degrading fatigue advantages of the composite construction Technical problems and achievements encoun- tered in the development process are discussed in terms of materials used, blade root design, manufacturing process, serviceability, and quality and safety control A plant has been constructed to satisfy future production requirements, with an anticipated product availability date of late 1984 R K R A82-40540 # Computer aided coordinate measuring systems. J W Nastn (United Technologies Corp, Sikorsky Aircraft Div , Stratford, CT) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982,p 371-376 Sikorsky's computer-aided inspection system and equipment utilized to assure that manufactured parts meet drawing tolerance specifications are discussed An overview of the system is given, and the software is described, including the monitor console routine and commands and the language commands The sys- tem's three coordinate measuring machines are discussed, and the part inspec- tion methods are described in stepwise fashion System benefits and time savings items are detailed, including quick and accurate measurement of parts difficult to inspect by conventional methods, significant reduction in inspection time, a con- sistent baseline that highlights variances, and the use of personnel with lower skill levels to effectively inspect critical parts C D A82-40541 # Support of the HH-65A - The impact of advanced tech- nology of VTOL systems upon existing product support. R E Walkup (Aerospatiale Helicopter Corp , Grand Prairie, TX) In American Helicopter So- ciety, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82- 40505 20-01) Washington, DC, American Helicopter Society, 1982, p 377-382 The Coast Guard (USCG) will begin to replace the HH-52 Helicopters with the HH-65A in 1982 The HH-65A is equipped with a state-of-the-art digital avionics system As the HH-52 has only vacuum tube avionics equipment, the new estab- lishment of a complete support capability for solid state digital avionics will be necessary in connection with the introduction of the HH-65A Other technological advances utilized in the HH-65A are related to turbine engines of modular design and the employment of composite materials in the aircraft structure The HH-52 will continue in operation until all USCG stations will have received their HH- 65A's To provide support for simultaneous operation of both helicopters without an increase in support personnel will necessitate careful planning during the transitional period Attention is given to the HH-65A avionics system, modular engine maintenance, aspects of corrosion control and the USCG mission, and the allocation and repair of spare components G R A82-40542 # A roadmap toward a fatigue qualification process for modern technology helicopters. S T -T Chiu and R W Arden (U S Army, Directorate for Development and Qualification, St Louis, MO) In American Heli- copter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 383-397 30 refs The helicopter fatigue qualification process is critically reviewed to establish a roadmap, providing specific directions for a more efficient and unified qualification process Specific improvements, various alternatives, and suggested unified ap- proaches are discussed in terms of suppormg rationales in the areas of coupon 501 A82-4Q543 S-N data utilization, S-N curve reduction factor and curve shape, cycle counting method, structure classification, fatigue test requirement and in-service monitor- ing Current status and an overview are presented of a parallel AGARD effort to compile a 'Helicopter Fatigue Design Guide' (Author) A82-40543 # Optimum structural design. R L Bennett (Bell Helicopter Textron, Fort Worth, TX) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 398-407 12 refs Four typical helicopter engineering analyses have been combined with a nonlin- ear programming (NLP) algorithm to produce closed loop design-oriented analy- ses The resulting models are shown to be very effective in supporting detailed design by eliminating the existing external man-m-the-loop iterative process The nonlinear programming problem and how it relates to the engineering design process is described, along with typical NLP algorithms and how they are com- bined with conventional engineering analyses C D A82-40544 # Design and fabrication of a composite rear fuselage for the UH-60 /Black Hawk/. D G Orlmo (U S Army, Applied Technology Labora- tory, Fort Eustis, VA) and B F Kay (United Technologies Corp , Sikorsky Aircraft Div , Stratford, CT) In American Helicopter Society, Annual Forum, 38th, Ana- heim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 408-416 The primary objective of the program to design a composite rear fuselage (CRF) is fabrication cost reduction, and other concerns are a 10% weight savings, improved reliability and maintainability, and increased ballistic survivability The CRF design comprises a stiffened skin, with five major panels, bulkheads, and frames A modular repair concept resulted in reduced life-cycle cost, introducing reliability and maintainability into the design In order to prevent fuel fires on impact with high explosive incendiary projectiles, rigid ballistic foam was used to fill the fuel cell Visual inspection as well as destructive tests were completed, and necessary tooling changes were implemented Objectives being met, a full-scale static test article is being produced R K R A82-40545 # In-plane shear test of thin panels. G L Farley and D J Baker (U S Army, Structures Laboratory, Hampton, VA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82- 40505 20-01) Washington, DC, American Helicopter Society, 1982, p 417-425 5 refs Efficient application of thin gage composite materials to helicopter fuselage structures necessitates that the materials be designed to operate at loads several times higher than initial buckling load Methods are required to accurately meas- ure and predict the response of thin gage composites when subjected to these loads This paper presents the results of an analytical and experimental study of the behavior of thin gage composite panels subjected to in-plane shear loads Finite element stress analyses were used to aid in the design of an improved shear fixture that minimizes adverse corner stresses and tearing and crimping failure modes characteristic of commonly used shear fixtures Tests of thick buckle resistant aluminum panels and thin aluminum and composite panels were conducted to verify the fixture design Results of finite element stress and buck- ling analyses and diagonal tension theory predictions are presented Correlation of experimental data with analysis indicated that diagonal tension theory can be used to predict the load-strain response of thin composite panels (Author) A82-40546 # A summary of weight savings data for composite VSTOL structure. R L Foye (U S Army, Research and Technology Laboratory, Moffett Field, CA) and R Arden (U S Army, Aviation Research and Development Command, St Louis, MO) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington. DC, American Helicopter Society, 1982, p 426-437 96 refs This paper summarizes the weight savings that have been obtained over the last ten years through the application of advanced composite materials to each of the major structural weight groups of a VSTOL airframe The data has been drawn from journal articles, published papers, R&D reports, and personal com- munications Helicopter, VSTOL, and fixed wing applications of composites have been included The data is not comprehensive but represents a significant sam- pling of all recent composite airframe designs . (Author) A82-40547 # Structural design of a crashworthy landing gear for the AH-64 Attack Helicopter. J M McDermott (Hughes Helicopters, Inc , Culver City, CA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 438-450 Requirements for the design of a landing gear for helicopters are considered In the case of the AH-64 Attack Helicopter, an additional consideration is related to air transportability requirements of the helicopter, necessitating a kneeling requirement in the landing gear configuration in order to reduce the height of the helicopter to fit into the cabin of the cargo aircraft transporting it This kneeling requirement was also utilized to provide a high degree of crash protection Ac- cording to specification, protection of the crew has to be provided for conditions involving a vertical impact velocity of as high as 42 ft/sec In order to meet this requirement, it was necessary to use the landing gear to absorb as high a proportion of the vertical kinetic energy as was feasible before the fuselage contacted the ground Attention is given to the configuration of the landing gear for the AH-64, the design criteria, details of impact energy absorption, the integra- tion of the landing gear into the airframe, and static structural testing G R A82-40548 # Ringfin augmentation effects. H E Lemont (Bell Heli- copter Textron, Fort Worth, TX) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7.1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 451-460 The nngfin concept has been developed since 1975 as a potential remedy for a number of concerns experienced in connection with the operation of single main totor/tail rotor helicopters This concept involves the use of a thrust ring around the tail rotor The ring acts as fin, and generates lift force (antitorque) The present investigation is concerned with the measured augmentation effects in ground running, in hover and side flight, in forward translation, and mixing of the rotor wakes The investigation shows that under static thrust conditions the tail rotor flow generates an induced positive force on the ring The rotor tip vortices are dissipated with downstream flow motion, and an expanding slowed-velocity wake is created G R A82-40549 * # Performance of the Rotor Systems Research Aircraft calibrated rotor loads measurement system. C W Acree, Jr (NASA, Ames Research Center, Moffett Field, CA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 461-473 6 refs The compound Rotor Systems Research Aircraft (RSRA) is designed to make high accuracy, simultaneous measurements of all rotor forces and moments in flight Physical calibration of the rotor force- and moment-measurement system when installed in the aircraft is required to account for any errors and to ensure that measurement system accuracy is traceable to the National Bureau of Stan- dards The first static calibration and associated analysis has been completed with good results Hysteresis was a potential cause of static calibration errors, but was found to be negligible in flight, and analytical methods have been devised to eliminate its effects on calibration data Flight tests confirmed that the cali- brated rotor loads measurement system performs as expected in flight, and that it can dependably make direct measurements of fuselage vertical drag in hover (Author) A82-40550 # Error minimization in ground vibration testing. E J Nagy (Kaman Aerospace Corp , Bloomfield, CT) In American Helicopter Society, An- nual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 474-480 5 refs The Ground Vibration Testing (GVT) of a U S Army AH-1G helicopter airframe has been successfully completed New methods have been developed to identify and minimize the errors in GVT These methods can be utilized in future pro- grams The new approaches make effective use of a digital signal analyzer as a 'working tool' Examples are presented to demonstrate the use of the digital signal analyzer in connection with a number of applications Attention is given to methods for the determination of the linear range, the location and identification of structural modes, the selection'of narrow band sweeps, the selection of driving points, the local mode effect, driving point acceleration mobility checks for posi- tive imaginary components, strain mobilities, the power method, and the number of averages G R A82-40551 # Results of the AH-64 Structural Demonstration. K R Spreuer (Hughes Helicopters, Inc . Carlsbad, CA) In Amenqan Helicopter So- ciety, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82- 40505 20-01) Washington, DC, American Helicopter Society, 1982, p 481-489 This paper presents (he results of the Structural Demonstration of the AH-64 Attack Helicopter The paper presents graphical data that shows the techniques used to attain the extreme points that define the flight envelope The areas of the flight envelope that most challenge the various components of the helicopter are discussed The methods used to assure flight safety during the program are also presented Finally, the most highly loaded components are identified and the conditions and causes of the loads are presented The Structural Demonstration was conducted successfully and all required maneuvers were performed without exceeding limit loads on any components (Author) A82-40552 # Evaluation of an automatic subsystem parameter moni- tor. R V Kurowsky and A S Santanelli (U S Army, Fort Monmouth, NJ) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 490-496 It is pointed out that the workload of the pilot of an aircraft is not necessarily reduced by making available to the pilot a new type of avionics system architec- ture, if the pilot is still required to perform all the tasks he has traditionally 502 A82-40878 performed To achieve such a reduction in workload, the pilot should be used primarily as a decision maker with the ability to reprogram and command his machine in flight The Electronic Master Monitor and Advisory Display System (EMMADS) is an information transfer system which will relieve the pilot of certain functions he has traditionally performed, such as monitoring aircraft subsystems A description is presented of the test procedures which will be used to evaluate the operator/control/display interface of the EMMADS Advanced Development Model G R A82-40553 * # The prediction of helicopter rotor discrete frequency noise. F Farassat (NASA, Langley Research Center, Hampton, VA) and G P Succi (Bolt Beranek and Newman, Inc , Cambridge, MA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings (A82- 40505 20-01) Washington, DC, American Helicopter Society, 1982, p 497-507 23 refs An accurate prediction of the noise produced by helicopters requires a good understanding of the noise generating mechanisms involved Such an under- standing can lead to controlling the noise of existing helicopters by avoiding noisy regimes of flight or by redesigning the mam and tail rotors The present investiga- tion is concerned with approaches which are suitable for the calculation of dis- crete frequency noise of helicopter rotors The governing differential equation of acoustics used in a consideration of acoustic formulations is the Ffowcs Williams- Hawkmgs (FW-H) equation Attention is given to a method reported by Farassat (1981), a method developed by Succi (1979), and a procedure discussed by Woan and Gregorek (1978) G R A82-40554 # A semiempirical high-speed rotor noise prediction tech- nique. K R Shenoy (Bell Helicopter Textron, Fort Worth, TX) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceed- ings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 508-516 14 refs A semiempirical technique to predict high-speed noise of helicopter main rotors is discussed This technique uses an existing data base, the properties of the equations governing the flow field, and empirical relationships to account for the changes in gross weight, blade chord and the blade rotational tip Mach number The technique is verified through an application to full-scale flyover noise data and full-scale in-flight noise data Hover test results for a model rotor are used to predict the noise levels for forward flight and are compared with wind tunnel test data In addition, results of flow field investigations to study the effects of blade design parameters on high-speed noise and to extend the prediction tech- nique are presented These results are based on the flow field calculations made by using a three-dimensional, quasi-steady, full potential transonic analysis devel- oped by NASA (Author) A82-40555 * # Dynamic surface measurements on a model helicopter rotor during blade slap at high, angles of attack. J E Hubbard, Jr andW L Harris (MIT, Cambridge, MA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7,1982, Proceedings (A82-40505 20-01) Washington, DC, American Helicopter Society, 1982, p 517-527 16refs Research supported by the Massachusetts Institute of Technology, Grant No NsG-1583 The modern helicopter offers a unique operational capability to both the public and private sectors However, the use of the helicopter may become severely limited due to the radiated noise generated by the rotor system A description is presented of some of the experimental results obtained with a model helicopter rotor in an anechoic wind tunnel with regard to blade stall as a source mechanism of blade slap Attention is given to dynamic rotor blade surface phenomena and the resulting far field impulsive noise from the model helicopter rotor at high angles of attack and low tip speed The results of the investigation strongly implicates the boundary layer as playing an important role in blade slap due to blade/vortex interaction (BVI) in a highly loaded rotor Intermittent stall cannot be ruled out as a possible source mechanism for blade slap This implies that blade surface characteristics, airfoil shape and local Reynolds number may now be used as tools to reduce the resultant far-field sound pressure levels in helicopt- ers G R A82-40556 # Helicopter model scale results of blade-vortex Interac- tion impulsive noise as affected by blade planform. D A Conner and D R Hoad(US Army, Structures Laboratory, Hampton, VA) In American Helicopter Society, Annual Forum, 38th, Anaheim, CA, May 4-7, 1982, Proceedings. (A82- 40505 20-01) Washington, DC, American Helicopter Society, 1982, p 528-537 21 refs An experimental investigation of the blade-vortex interaction impulsive noise characteristics of an advanced mam rotor system for the UH-1 helicopter has been conducted Models of both the advanced mam rotor system and the stan- dard UH-1 mam rotor system were tested at one-quarter scale in the Langley 4- by 7-Meter (V/STOL) Tunnel using the General Rotor Model System (GRMS) Tests were conducted over a range of descent angles which bracketed the blade-vortex interaction phenomenon at a range of simulated flight speeds The tunnel was operated in the open-throat configuration with acoustic treatment to improve the acoustic characteristics of the test chamber The model data in- dicated that the advanced rotor system has increased the flight-scaled, LA noise produced by the UH-1 at all descent angles except where the blade-vortex interaction phenomenon was most intense for the standard UH-1 mam rotor system (Author) A82-40561 # Research on the behavior of a turbojet engine during internal and external disturbances with respect to early recognition of damage (Untersuchungen uber das Verhalten eines Turbostrahltnebwerks be! Inneren und ausseren Storungen im Hinblick auf die Schadensfriiher- kennung). H TonskOtter Aachen, Rheinisch-Westfalische Technische Hoch- schule, Fakultat fur Maschmenwesen, Dr-Ing Dissertation, 1980 215 p 41 refs In German The results of a theoretical and experimental study on the behavior of a single- wave turbojet engine during disturbances are presented The simulated distur- bances are categorized as either external or internal The former influence flow relationships in the engine and vary their behavior, but entail no consequences for the engine parts Damage and structural changes in the engine components are called internal disturbances Experimentally obtained thermodynamic param- eter changes are presented as volume divisions and average values A program to calculate the stationary and dynamic operating behavior in turbojet engines is used to determine the extent to which the experimental results coincide with a one-dimensional computational procedure, and whether monitoring of operating behavior can be useful for early detection of damage C D A82-40562 # Research on an adaptive Kalman filter for solving the radar tracking problem (Untersuchung adaptiver Kalman-Filter zur Lb'sung des Radar-Zielverfolgungsproblems). W Schumacher Berlin, Technische Universitat. Fachbench Verfahrenstechmk, Dr-Ing Dissertation, 1979 126p 44 refs In German Research supported by the Deutsche Forschungsgememschart The use of Kalman filters in automated air traffic control for failsafe measure- ment of local coordinates and speeds is discussed Continuous and time-discrete models are constructed and an optimal filter is investigated A sensitivity analysis is presented, followed by the design and simulation of an adaptive filter Tracking at a one-level trajectory is discussed, and the design of an adaptive procedure is analyzed for different filter levels C D A82-40569 # Design and construction of a flexible autonomic elec- tronic display device (Entwurf und Aufbau eines flexiblen aulonomen elek- tronischen Anzeigegerates). R Frielmg Braunschweig, Technische Universitat, Fakultat fur Maschmenbau und Elektrotechnik, Dr -Ing Dissertation, 1980 166 p 40 refs In German A compact, autonomic display device for presenting synthetic graphic images is needed for research work in the area of flight control The device should also be suited for the presentation of dynamic processes A device with the desired characteristics is currently not commercially available The present investigation is concerned with the essential design criteria for the development and the con- struction of a display device which satisfies the considered requirements The envisaged device consists of a microcomputer and an image element generator which contams~digital differential analyzer (DDA) circuits A detailed mathemati- cal description of the generation of conic sections as image elements and the linear transformation of the elements provides the basis for universal employment possibilities of the device The performance characteristics of the display device are illustrated with the aid of two examples, including an interpolation problem, and the display of data for flight control applications G R A82-40876 International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings. Volumes 1 & 2. Edited by B Laschka and R Staufenbiel, New York, American Institute of Aeronautics and Astronautics, 1982 Vol 1. 821 p, vol 2,721 p Members, $75 , nonmembers, $90 In English and French (For individual items see A82-40877 to A82-41025) Topics in aeronautical and aerodynamics research, development, implementa- tion, and future directions are considered The development and applications of Space Transportation Systems are described, and attention is also given to development programs for transport aircraft and military combat aircraft Theoretical studies in flowfields, crew station design, and power plant materials and design are presented, along with investigations of aerodynamics, computa- tional aerodynamics, control systems, and materials fatigue and tolerance The uses of simulators for Orbiter pilot training, swept wings for efficient flight, and computer-controlled flight management systems are described, and examina- tions of vortex flows, structural dynamics, applications of composite structures, and canards are reported M S K A82-40878 # Engineering aspects of international collaboration on Tornado. B O Heath (British Aerospace Public, Ltd , Co , Aircraft Group, Pres- ton, Lanes, England) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, $3gis*! 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, 503 A82-40879 American Institute of Aeronautics and Astronautics, 1982, p 8-22 11 refs Design features, engineering goals, and the performance envelope of the Tor- nado combat aircraft are described The fighter was developed to perform air-to- ground, mterdictor/stnke, naval strike, reconnaissance, air superiority, interception, and training missions The distribution of responsibilities and man- agement authority among the organizations of the three nations which participa- ted in the development program are outlined, along with decisions in the evolution of the design A new engine was developed as a cost-saving measure, and the aircraft was built to ensure that no single failure would endanger flightworthmess Easy access was also added to the Tornado systems in order to hold down repair time and costs M S K A82-40879 # Advanced aerodynamic design for future combat air- craft. BRA Burns (British Aerospace Public, Ltd , Co , Preston, Lanes , En- gland) In- International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 23-33 Progress in aerodynamic design features to enhance the effectiveness and performance of combat aircraft are reviewed Higher turning performance at subsonic and transonic speeds has been achieved through improvements in the lift/drag ratio by providing for attached flow on the upper part of the wings The effects of wing root leading edge strakes and aeroelastic tailoring on flight per- formance are discussed, and methods of augmenting the turning performance by adding wing interference to the jet exhaust are considered Pilot workload has been lowered by active flight controls, which allow full exploitation of modern aircraft flight and maneuvering envelopes, while gust alleviation has ensured stable flight during high speed, low altitude flight Intake duct geometry has been configured to permit operation at high angles of attack and in sideslip, while an underfuselage carriage scheme has been developed which greatly reduces inter- ference drag compared with conventional underwmg carriage M S K A82-40880 # Some aerodynamic/flightmechanic aspects for the de- sign of future combat aircraft. P Mangold (Dormer GmbH, Friednchshafen, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, Au- gust 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, Ameri- can Institute of Aeronautics and Astronautics, 1982, p 34-43 6 refs At an early project state of a future combat aircraft, designed with negative static stability, it is necessary to go through an optimization process in order to minimize the complexity and cost for the control system by avoiding undesirable aerodynamic characteristics A careful refinement of certain parts of the configu- ration gives the chance to stay within the limits and to meet the criteria and goals for the desired longitudinal and lateral basic behavior General trends, evaluated from many wind tunnel tests, are presented which show the influence of changing LEX size, shape of fuselage nose, slats, vertical tails etc Concerning maximum attainable negative static margin one limit is set by the time to double amplitude after a gust disturbance Looking at some typical existing and projected combat aircraft the paper discusses the fact and the consequences that the same Time To Double leads to different (attainable) static margins (Author) A82-40881 # Gust load alleviation on Airbus A 300. O Sensburg, J Becker, H Lusebrmk, and F Weiss (Messerschmitt-Bdlkow-Blohm GmbH, Mu- nich and Hamburg, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 44-58 15 refs An active gust load alleviation system for an Airbus A 300 with a 10% wing span increase is described, along with passive maneuver load alleviation The introduc- tion of active control systems is intended to minimize the incremental structural dynamic loads caused by span expansion or increased wing loading, especially due to gusts The gust magnitude is assayed by a vane or differential pressure sensor in the front fuselage, weighted with a time delay for the vane to wing transit Actuator transfer functions are introduced into the existing active flight controls to compensate to, unsteady aerodynamic effects A block diagram of the closed loop gust alleviation system is provided, along with linearized equations of motion of elastic aircraft with closed or open loop systems Finally, further studies are indicated in unsteady effects in order to implement passive maneuver load alleviation M S K A82-40882 # Calculations of transonic steady state aeroelastic ef- fects for a canard airplane. N Agrell and S G Hedman (Flygtekniska Forsok- sanstalten, Bromma, Sweden) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982. p 59-66 5 refs Forsvaret Matenelverk Contracts No AU-1540,No AU-1691 A transonic small perturbation potential method for calculation of the aeroelas- tic effects on aircraft with a canard is presented, and comparisons are made with results of earlier calculations The equation for the disturbance potential is de- fined and the velocity potential is transformed into a finite difference form Bound- ary conditions are formulated for subsonic and supersonic regimes and methods of treating steady state aeroelastic effects are discussed A numerical mesh is devised using the SAAB 37 Viggen as an example and solution procedures at sub- and supersonic speeds are presented, covering the speed range of Mach 0 9-1 1 Aeroelastic deformation is calculated by balancing aerodynamic loads against interior forces M S K A82-40883 # Computer-aided derivation of equations of motion for rotary-wing aeroelastic problems. F Kiesslmg (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Institut fur Aeroelastik, Gottmgen, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 67-77 13 refs A general computer-algebra system has been applied to derive literal equa- tions of motion for the aeroelastic behavior of rotary-wings Inertia, elastic, struc- tural damping, aerodynamic, and gravitational contributions are considered Modal degrees of freedom are provided to represent elastic rotor blades The program input comprises mainly a kinematic description of the system A weight- ing scheme is used to obtain the most important terms in a consistent manner Multiblade coordinate transformation is applied to reduce or to eliminate periodic coefficients As output, matrices are written in FORTRAN code, which reflect the mathematical model and can be used for further numerical calculations As an example, the suggested procedure is applied to a model of a two-bladed wind turbine mounted on an elastic tower (Author) A82-40884 # HAJIF-II -A program system for the dynamic analysis of aeronautical structures. G -G Liu and J -J Li (Chinese Aeronautical Establish- ment, Beijing, People's Republic of China) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 78-82 17 refs HAJIF-II is a program system developed for the calculation of modal parame- ters of aircraft structures as well as flutter and gust response analyses with active control systems taken into consideration Ninety-nine substructures, each with 7000 degrees of freedom, can be used in the calculation of modal parameters and 50 modes for the flutter and gust response analyses Some new techniques, such as a revised hypermatnx technique, an improved algorithm of simultaneous iteration, and new methods of modal synthesis etc . were developed to improve the efficiency of the system Typical aircraft structures were analyzed and good results were obtained (Author) A82-40886 # A practical approach to the incorporation of technical advances in avionics. J D Bannister and D Roughton (British Aerospace Public, Ltd , Co , Aircraft Group, Brough, North Humberside, England) In Interna- tional Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Pro- ceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 97-107 Features of a program to design, develop, and construct an avionic system demonstrator rig for the next generation of tactical combat aircraft while taking advantage of advances in VLSI hardware are described The VLSI-based archi- tecture permits shared communication and displays, in addition to sensor- dedicated microprocessors Military standard data busses can currently handle up to 31 subsystems through a common transmission line, and further determina- tions are needed to identify the effects of common mode failures, limitations on the amount of traffic on a bus, the effects of transmission delays, and particular links which cannot be routed through a data bus Details of the functional aspects of pilot, system control, mission, navaids, and aircraft groups to define problem areas, goals, and method to allow an acceptable transition to VLSI-based avion- ics are discussed M S K AB2-40887 # Applying advanced technology to flight station design. W R Paden, Jr and G A Sexton (Lockheed-Georgia Co . Marietta, GA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle. WA. August 22-27.1982. Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 108-117 Efforts by Lockheed to develop a flight simulation research facility are de- scribed, including the construction of a'funclional pilot's desk flight station, aircraft systems, and controls expected to be in use in the 1990s Simulators are being constructed to accommodate high resolution CRT color graphics, flat panel dis- plays, touch panel controls, voice command and response systems, head-up displays, and electronic flight and thrust controllers Stages in the realization process are outlined, noting current status in the design and fabrication of the simulator hardware and software Systems under study are an appropriate color format, display formats, and advisory, caution, and warning system and cockpit 504 A82-40896 display of traffic information format Further research on the effects of introduc- tion of the new equipment on pilot performance and on air traffic control are indicated M S K A82-40888 # The evolution of display formats for advanced fighters using multimode color CRT displays. N M Lefritz, J H Turtle, Jr (Rockwell International Corp . El Segundo, CA), and M J Forte (Bendix Corp , Teterboro, NJ) In International Council of the Aeronautical Sciences, Congress. 13th and AIAA Aircraft Systems and Technology Conference. Seattle, WA, August 22-27, 1982. Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 118-131 Research supported by the Rockwell Independent Research and Development Fund Efforts to combine electromechanical indicators, instruments, and displays onto multimode, time-shared CRT displays (MMD) in advanced cockpit configura- tions for military aircraft are described A cockpit configuration is presented in which the stick controller is situated to the right of the pilot, while the center console contains three MMDs Color formatting was guided by goals to minimize electromechanical displays, provide the pilot with information relevant solely to a given mode of operation, have all data available at the pilot's option, use color and formats already implemented by the military, replace symbolic information with pictorial information, and employ the CRT for checklists Procedures for completing an electronic preflight checklist are detailed, in addition to take-off, climb to cruise, emergency conditions, and landing sequences M S K A82-40889 # Application of advanced exhaust nozzles for tactical aircraft. D L Bowers and J A Laughrey (USAF, Wright Aeronautical Laborato- ries, Wright-Patterson AFB, OH) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 132-141 39 refs Advanced exhaust nozzles play an important role in the system design for advanced tactical aircraft and offer attractive design options which contribute to total aircraft performance These exhaust nozzles can improve aircraft cruise performance if integrated carefully Thrust vectoring attainable with these ex- haust nozzles adds significantly to aircraft maneuver performance STOL per- formance is obtained by thrust reversing or a combination of thrust reversing and thrust vectoring The significant aircraft performance improvements which lie in advanced exhaust nozzle technology will be determined by past, ongoing and future programs investigating the best application of advanced exhaust nozzles for tactical aircraft (Author) A82-40890 # Optimized 10 ton class commercial aircraft engine. R Laurens (SNECMA, Moissy-Cramayel, Seine-et-Marne, France) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 142-145 The development program goals and methods for the CFM56 series engines for powering aircraft of 110 to 200 passengers into the 1990s are reviewed The CFM56, in the 20,000 Ib class, began with the F101 core Derivatives of the engine are currently used in the DC8-60. the KC-135 tanker, and the 737 Com- pression ratios have been raised from 25-30 1 to 35-40 1, and the core features a low clearance compressor with rotor temperature control, variable stators on the first four stages, a high speed HP turbine, active clearance cooling in the turbine, and close turning clearances High energy X rays are being employed to improve the clearances and survey the temperature map and cooling system A commonality of 60% has been maintained between generations of the engine MSK A82-40891 # Recent advances in the performance of high bypass ratio fans. D J Nicholas and C Freeman (Rolls-Royce, Ltd , Derby, England) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 146-158 7 refs Research supported by the Ministry of Defence (Procurement Executive) Theoretical and experimental techniques employed to improve the efficiency of the high tip speed fan jet engine are reviewed, Design features of high bypass ratio fans, including arrangement of the fan diffusion factors induced by the placement of the outlet guide vanes and the splitter are discussed Overall design parameters of the RB211-22 fan are described, including factors influencing the spanwise work distribution, the outlet guide configuration, and techniques for characterizing the airflow It was found that an optimum tip speed existed for each level of design pressure ratio Performance tests on scale model rigs to deter- mine the spanwise distribution, the blade element performance, and airfoil losses, were compared with actual engine operation It is noted that laser holography, anemometry, and two- and three-dimensional numerical models were employed to identify and define the flow in test rig conditions MSK A82-40892 # Axisymmetric approach and landing thrust reverser im- pacts on usage and LCC. J P Blackman.P B Stumbo (USAF, Aero Propulsion Laboiatory, Wright-Patterson AFB, OH), and M F Eigenmann (McDonnell Air- craft Co , St Louis. MO) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27.1982, Proceedings Volume 1 (A82-40876 20-01) New York. American Institute of Aeronautics and Astronautics, 1982, p 159-167 7 refs The effects on the performance of the F15-C and advanced fighters by the installation of three different types of approach and landing thrust reversers (ALTR) are reported, including projected impacts on thy life cycle costs (LCC) The aircraft were tested in mission configurations comprising a 350 nm subsonic cruise and 200 nm supersonic dash at high altitude, along with appropriate defen- sive maneuvers The ALTR concepts examined included a rotating vane up- stream of the nozzle throat, a translating shroud ALTR downstream of the throat, and a three-door ALTR downstream of the nozzle throat of the advanced air-to- surface vehicle Effects were evaluated in terms of the resultant engine hot time, and cycles of use of the ALTRs in a variety of mission modes The F15-C LCC was estimated to cost 3 8% more using the ALTR, while advanced vehicle LCCs increased 24-38%, with smallest increases occurring with'downstream ALTR placement MSK A82-40893 * # Observations and implications of natural laminar flow on practical airplane surfaces. B J Holmes (NASA, Langley Research Center, Hampton, VA) and C J Obara (Kentron Technical Center, Hampton, VA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 168-181 48 refs The results of natural laminar flow (NLF) experiments conducted by NASA to determine if modern aircraft structures can benefit from NLF as do sailplanes are presented Seven aircraft, ranging from a Cessna 210 to a Learjet 28/29, with relatively stiff skins were flown in production configurations with no modifications Measurements were made of the boundary-layer laminar to turbulent transition locations on various aerodynamic surfaces, the effect of a total loss of laminar flow, the effect of the propeller slipstream on the wing boundary-layer transition and the boundary-layer profiles, the wing section profile drag, the effect of flight through clouds, and insect debris contamination effects Favorable pressure gradients for NLF were concluded to be feasible up to a transition Reynolds number of 11 million Laminar flows were observed in propeller slipstreams, and insects were found to cause transition 1 /4 of the time MSK A82-40894 # Aerodynamic development of laminar flow control on swept wings using distributed suction through porous surfaces. J A The- lander, J B Allen, and H R Welge (Douglas Aircraft Co . Long Beach, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 182-189 8 refs Development of a laminar flow control system utilizing distributed suction through porous strips is reviewed Recent improvements in electron beam perfor- mation technology have greatly enhanced the potential for practical LFC applica- tion The design of airfoil shapes compatible with LFC on swept wings is outlined Boundary layer stability analysis results and determination of suction distributions are reviewed Considerations for an operational system for protection from ice and insect contamination are noted Results of a swept wing model test and plans for a LFC leading edge glove flight test program are reviewed (Author) A82-4089S # External aerodynamic design for a laminar flow control glove on a Lockheed JetStar wing. J A Bennett and L B Brandt (Lockheed- Georgia Co , Marietta, GA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 190-202 34 refs A recent study contract for a subsonic laminar flow control (LFC) transport with a supercritical wing and recent Lockheed research are discussed as background information leading to the design of a JetStar part-span LFC glove to be flight- tested The special design requirements needed to develop the glove and some of the problems encountered during the process are presented The following topics are discussed a method of simulating the interference effects of the body/pylons/nacelles on wing pressures when using an isolated-wing code, wind-tunnel testing of a JetStar model with a wing glove and correlation with theoretical glove pressures, and suction requirements for maintaining a laminar boundary layer (Author) A82-40896 * # NASA research on viscous drag reduction. R H Pe- tersen and D V Maddalon (NASA, Langley Research Center, Hampton, VA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p. 203-213 42 refs 505 A82-40897 Current NASA research points toward exciting opportunities for large reduc- tions in viscous drag Research is underway on natural laminar flow, laminar flow control by suction, and turbulent drag reduction Preliminary results suggest that a significant amount of natural laminar flow can be achieved on small, straight- wing airplanes On larger, swept-wmg aircraft, laminar flow control by distributed suction is expected to result in significant fuel savings The area over which laminar flow control is applied depends on tradeoffs involving structural com- plexity, maintenance, and cost Several methods of reducing turbulent skin fric- tion by altering the turbulence structure itself have shown promise in exploratory testing This paper reviews the status of these technologies and indicates the benefits of applying them to future aircraft (Author) A82-40897 # Viscous transonic airfoil flow simulation. J Longo, W Schmidt (Dormer GmbH, Fnednchshafen, West Germany), and A Jameson (Dor- mer GmbH, Fnednchshafen, West Germany, Princeton, University, Princeton, NJ) In International Council of the Aeronautical Sciences, Congress, 13th and A1AA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 214-223 19 refs The present paper describes a method for the calculation of subsonic and transonic viscous flow over airfoils using the displacement surface concept This modelling technique uses a fast multigrid solver for the full potential equation and laminar and turbulent boundary layer integral methods In addition, special mod- els for transition, laminar or turbulent separation bubbles and trailing edge treat- ment have been selected However, the flow is limited to small parts of trailing edge-type separation The present paper deals with some theoretical features in a short description and shows computed results compared with experimental data and other methods (Author) A82-40898 # Computation of supersonic flow around three-dimen- sional wings. B G Arlmger (Saab-Scama AB, Lmkopmg, Sweden) In Interna- tional Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Pro- ceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 224-232 16 refs As part of the development of a program for supersonic flow around realistic aircraft configurations a method is presented for the computation of strictly super- sonic flow around single wings or two-wing configurations of arbitrary shape The method is based on the steady Euler equations which are solved in a streamwise marching procedure using a shock-capturing finite volume formulation As solu- tion algorithm an explicit predictor-corrector scheme of MacCormack type is used A variety of numerical applications of the method is presented including canard configuration cases, and comparisons are made with other theories and test data confirming versatility and reliability of the method (Author) A82-40899 # Transonic small disturbance code for body-wing con- figuration coupled with full potential code for wing alone. A Luntz (Israel Aircraft Industnes, Ltd , Lod, Israel) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 233-237 7 refs A transonic small disturbance approximation code TSD was designed, for potential flow around a body-wing configuration This code is based on the em- bedded fine grid concept elaborated by Ch Boppe Improvements are introduced into the boundary condition representation, including the body boundary condi- tion, the wing boundary condition and the interface between the fine grid box and the coarse grid computation Only cartesian coordinate grids are used The code provides good prediction of the position of the shock on the wing surface, using a comparatively small number (about 20) of grid points along the wing section cord The TSD code is coupled with a modified (no crossflow at the wing root plane) in FL022, is replaced with the crossflow values computed by the TSD code This new boundary condition, at the wing root, contains all information of the body influence needed for the wing pressure computation The coupling allows detailed analysis of the body-wing interference effects in the flow (Author) A82-40900 # Advanced fighter technology integration program AFT- l/F-16. A J Bianco and F R Swortzel (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB, OH) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, Amencan Institute of Aeronautics and Astronautics, 1982, p 238-246 The AFTI/F-16 Advanced Development Program is developing and flight vali- dating advanced technologies which improve fighter lethality and survivability The capability is achieved by the integration of mission task-tailored, dig.tal flight controls with a director-type fire control system, and advanced target sensor/- trackers The Digital Flight Control System is the core technology Integration of the systems forms the capability for automated maneuvering attack Evaluation of automation, with respect to the weapon delivery task, is a key program thrust Use is made of nonconventional aircraft control modes to achieve improved maneuverability and weapon line pointing Careful attention is given to pilot/vehi- cle interface provisions The AFTI/F-16 is now undergoing an extensive test program to provide the confidence necessary to transition the technologies for use on current and future fighter aircraft (Author) A82-40901 # Tail versus canard configuration - An aerodynamic com- parison with regard to the suitability for future tactical combat aircraft. G Wedekmd (Dormer GmbH, Fnednchshafen, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, Amencan Institute of Aeronautics and Astronautics, 1982, p 247-254 Extensive experimental and theoretical research work on tail and canard con- figurations has recently been done at Dormer, considering the requirements for a future tactical combat aircraft Tail and canard configurations, which were designed for the same tactical requirements, are compared This comparison leads to the conclusion that the canard configuration cannot be regarded superior to the tail configuration, neither with regard to zero-lift drag at supersonic speeds nor with regard to lift-dependent drag at subsonic and supersonic speeds Fur- thermore, severe problems must be expected regarding lateral and directional stability at high angles-of-attack for a canard configuration It turns out that those problems do not occur or are easier to handle with tail configurations (Author) A82-40902 # Material and process developments on the Boeing 767. J T Qumlivan and D T Lovell (Boeing Commercial Airplane Co , Seattle, WA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 255-261 The design goal of the 767 is an economic service life of 20 years with minimum unscheduled maintenance Materials, material processing, and assembly meth- ods employed on the 767 play a key role in the achievement of this design goal Materials and processes also are key in maintaining weight within design limits for fuel efficiency The 767 uses a wealth of new and improved materials, pro- cessing methods, and assembly techniques Some of the innovations are subtle and involve minor changes to previous technology, such as the reduction of certain fastener head diameters Others are more dramatic, such as the use of new aluminum alloys for wing skins or advanced composites for primary flight- control surfaces Corrosion resistance is achieved through material selection, attention to design details, and proper finishing and sealing methods For the most part, the materials selected for the passenger cabin interior are new and are selected for their flame resistance and lack of smoke and toxicant emission during combustion A review of major structural and nonstructural material and process developments on the 767 will be summarized in this paper (Author) A82-40903 # The promise of laminated metals in aircraft design. D H Petersen, L E Sloter, II, W A Poindexter, J L Mans, and G E Kuhn (Vought Corp, Dallas, TX) In International Council of the Aeronautical Sciences, Con- gress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 262-269 8 refs The relative merits of monolithic metals, adhesively bonded sheet metal and a new family of metallurgically bonded laminated alloys are presented and dis- cussed in light of the U S Air Force's laminated metal technology demonstration Advanced Technology Wing program A wing section was designed and con- structed whose lower skin consisted of adhesively bonded aluminum layers hav- ing no fastener penetrations The elimination of lower wing skin fasteners precludes both corrosion intrusion sites and locations for structural cracking, and in addition reduces manufacturing and assembly costs The wing suffered no damage during two lifetimes of spectrum fatigue testing, as well as an additional 1 8 lifetimes of damage tolerance testing which included exposure to sump water and JP-4 fuel O C A82-40904 # Design of compensated flutter suppression systems. • M Lanz and P Mantegazza (Milano, Politecmco, Milan, Italy) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 270-279 37 refs Consigho Nazionale delle Ricerche Contract No 81,02536,07 The paper presents a method to design compensated flutter suppression sys- tems by eigenvalue assignment The compensator is designed as a state ob- server by paralleling the Luenberger approach The eigenvalues of the aeroelastic system and compensator are obtained by imposing a stationary value to a suitable norm of the gains, under the constraint of satisfying the aeroelastic eigensystem for assigned stable eigensolutions, and without any problem on the modelling of the unsteady aerodynamic forces The compensator can be used not only to reconstruct lacking states, but also to insure msensitivity to different flight 506 A82-40912 conditions A method is presented to mechanize, and possibly to reduce in order, the aeroelastic observer Some simple examples illustrate the use of the method along with comments on the stabilization of an aeroelastic system by eigenvalue assignment techniques (Author) A82-40905 # Design and experience with a low-cost digital fly-by- wire system in the SAAB JA37 Viggen A/C. K Folkesson, P 0 Elgerona, and R Haglund (Saab-Scama AB, Linkopmg, Sweden) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA. August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 280-288 Research supported by the Forsvaret Matenelverk A digital Fly-By-Wire system has been designed built and evaluated as a rig system and as a flight system installed in a JA37 Viggen test aircraft Headlines for definition of the system have been low complexity and low production cost, met by trading off complexity against safety and reliability margins System characteristics are minimized servo hardware, minimized channel interconnec- tions and maximum replacement of hardware by software including servo loop closures Functional development areas are application of optimal control tech- nique for multimode laws and for servo loop computations The paper will present system definition, system mechanization in test aircraft, ground test and flight test information (Author) A82-40906 * # Design and flight testing of a digital optimal control gen- eral aviation autopilot. J R Broussard (Information and Control Systems, Inc , Hampton, VA), D R Downing (Kansas, University, Lawrence, KS), and W H Bryant (NASA, Langley Research Center, Flight Control Systems Div , Hampton, VA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 289-298 12refs Contract No NAS1- 16303 This paper presents the designs of Proportional-lntegral-Filter (PIF) autopilots for a General Aviation (NAVION) aircraft The PIF autopilots use modern control theory to determine heading select and altitude select and hold autopilot modes The PIF control law uses typical General Aviation sensors for state feedback, command error integration for command tracking, digital complimentary filtering and analog prefiltering for sensor noise suppression, a control filter for computa- tion delay accommodation, and the incremental form to eliminate trim values in implementation Theoretical developments'for the control law are described which combine the sampled-data regulator with command generator tracking for use as a digital flight control system The digital PIF autopilots are evaluated using closed-loop eigenvalues and simulations Successful flight test results for the PIF autopilots are presented for different turbulence conditions and quadratic weights (Author) A82-40907 # Preliminary design of an advanced integrated power and avionics information system. G L Dunn, P Leong (Boeing Military Air- plane Co , Seattle, WA), and D Fox (USAF, Aero Propulsion Laboratory, Wright- Patterson AFB, OH) In International Council of the Aeronautical Sciences, . Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 299-305 Contract No F33615-80-C-2004 An advanced aircraft electrical system is described which meets the require- ments for a 1990 time frame two-engine tactical aircraft with multimission capabil- ity It features modular design and use of intelligent electrical load management centers with solid state power controllers, resulting in a greatly enhanced aircraft electrical system over that currently avajable The power generation and distri- bution, electrical power control, multiplex data bus characteristics, power system processor, electrical load management center, generator control unit, and electri- cal system software are discussed and diagrammed C D A82-40908 * # Inlet and airframe compatibility for a V/STOL fighter/at- tack aircraft with top-mounted inlets. D A DurstonandD B Smeltzer (NASA, Ames Research Center, Moffett Field, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982. Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 305/3-305/1 9 refs Aeiodynamic force and inlet-pressure data were obtained for 9 5% force and pressure models of a V/STOL fighter/attack aircraft configuration with top- mounted twin inlets Data are presented from wind tunnel tests conducted at Mach numbers of 0 6, 0 9, and 1 2 at angles of attack up to 27-deg and angles of sideslip up to 12-deg Trimmed aerodynamic characteristics and inlet perform- ance were compared for three different leading-edge extension (LEX) configura- tions The effects of wing leading- and trailmg-edge flaps on the inlet were also determined Maneuver performance was calculated from combined force and inlet-pressure data The largest of the three LEX sizes tested gave the best airplane maneuver performance Wing flap deflections improved inlet recovery at all Mach numbers (Author) A82-40909 # Investigation of the unsteady airloads on a transport aircraft type airfoil with two interchangeable oscillating trailing edge flaps, at transonic speed and high Reynolds numbers. H Triebstem (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Gottingen, West Ger- many), R Destuynder (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seme, France), and H Hansen (Messerschmitt-Bolkow-Blohm GmbH, Hamburg, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 306-315 8 refs Research supported by the Bundesmmistenum fur Forschung und Technology Investigations in unsteady aerodynamics were conducted in order to study the potential of active control technology for transport aircraft wings Wind tunnel tests were carried out using a large two-dimensional model with two interchange- able, fast moving, trailing edge control surfaces of different relative chord The subsonic and supercritical pressure distributions were studied, and the unsteady aerodynamic coefficients were analyzed It is found that in subsonic flow trailing edge separation causes considerable reduction in steady lift, but there is far less influence on the magnitude of the unsteady lift generated by an oscillating control surface Only the corresponding phase angle changes dramatically In transonic flow the development of the supersonic region and the shock strength and loca- tion demonstrate a predominant influence on steady as well as unsteady pres- sure distributions The properties of the supersonic regions and the shocks change considerably with all parameters investigated C D A82-40910 # Determination of the efficiency of a trailing edge flap in unsteady three-dimensional flow (Determination de I'efficacite' d'un volet de bord de fuite en ecoulement tridimensionnel instationnaire). H Consigny (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seme, France) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 316-328 18 refs In French Research supported by the Direction des Recherches, Etudes et Techniques and Mmisterede la Defense A study was carried out in order to improve understanding of the three-dimen- sional unsteady effects of an oscillating part-span trailmg-edge flap The experi- ments were performed on a constant chord and constant thickness supercritical wing mounted on the sidewall of a transonic wind tunnel The model was fitted with some 238 static pressure taps and 136 small unsteady pressure transducers located on several spanwise stations The measurements made for different geometric configurations provided extensive information on the influence of vari- ous parameters on both steady and unsteady chordwise pressure distributions and aerodynamic coefficients The experimental results were compared with those obtained by theoretical methods based on the solution of the full potential equation in steady flow and on the classical transonic small disturbances equa- tion in unsteady flow Quasi-steady pressure distributions were also compared to preliminary computational results, including viscous effects C D A82-40911 * # An investigation of scale model testing of VTOL aircraft in hover. W G Hill, Jr, R C Jenkins (Grumman Aerospace Corp , Bethpage, NY), and M R Dudley (NASA, Ames Research Center, Moffett Field, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 329-335 6 refs Contract No NAS2- 10645 Utilizing the unique opportunity created by full scale hover testing of the twin-jet Grumman Design 698 VTOl aircraft in the NASA-Ames Hover Facility, a series of experiments was conducted to evaluate the effectivness of scale model testing in predicting full scale behavior Interference forces were found to be sensitive to aircraft lower surface geometry, but when the geometry was modeled accu- rately the small scale results matched full scale forces guite well The interfer- ence forces were found to be insensitive to core nozzle temperature and fan nozzle pressure ratio The results clearly demonstrate that small scale models can be reliably utilized for aircraft and technology development when the appro- priate sensitivities are recognized (Author) A82-40912 # Optimization of flight with tilt wings (Optimisation du vol a aile battante. P Contensou (ONERA, Chatillon-sous-Bagneux, Hauts-de- Seme, France) In International Council of the Aeronautical Sciences. Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, Au- gust 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, Ameri- can Institute of Aeronautics and Astronautics, 1982, p 336-341 In French Within a structure of simplifying assumptions, a complete solution is presented for the problem of optimizing a tilted flying surface by establishing the law of motion relative to a mobile wing and determining the functions of lift and propul- 507 A82-40915 sion for a heavy and mertial body The solutions are compared both with bird flight and mechanical flight C 0 A82-40915 * # Advanced technologies applied to reduce the operating costs of small commuter transport aircraft. O Masefield, A Tun, and M Remicke (Pilatus Aircraft, Ltd , Stans, Switzerland) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, P 352-358 NASA-supported research The application of new aerodynamic, structural, and propulsion technologies to a specified baseline commuter aircraft is studied The assessment models can be used on a desktop calculator and include a sizing program, operating cost program, and passenger ride qualities model Evaluation is done with a step-by- step approach and is applied to range, number and type of engines, structure, wing selection, and configuration A 40 percent direct operating cost saving is anticipated compared to current well established commuter aircraft C D A82-40917 # Design and experimental verification of the USB-flap structucture for NAL STOL aircraft. M Sano (National Aerospace Laboratory, Tokyo. Japan), Y Fu|imon (National Space Development Agency, Tokyo, Japan), and S Maekawa (Kawasaki, Heavy Industries, Ltd , Gifu, Japan) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 370-375 6 refs In order to verify the safety of the USB flap structure of the NAL STOL experi- mental aircraft, tests were carried out on structural models, including a test to detect thermal buckling temperature, vibration tests, and an acoustic fatigue test at elevated and room temperature The USB flap structure, the acoustic fatigue design, the structure and static and dynamic characteristics of the test panel are discussed, including the resonant frequency, mode shape and damping coeffi- cient, static thermal response, and dynamic response It was found that thermal buckling occurred on test panels, that resonant frequencies of the flat test panels fall in the range between those of clamped and those of simply supported plates, and that through the prescribed fatigue test period, all structural models proved themselves to be strong enough to resist both acoustic and thermal loading CD A82-409Z1 * # A summary of V/STOL inlet analysis methods. D P Hwang and J M Abbott (NASA, Lewis Research Center, Cleveland, OH) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 402-409 24 refs The methods used to analyze the aerodynamic performance of V/STOL inlets at the NASA Lewis Research Center are briefly described Recent extensions and applications of the method are emphasized They include the specification of the Kutta condition for a slotted inlet, the calculation of suction and tangential blowing for boundary layer control, and the analysis of auxiliary inlet geometries A comparison is made with experiment for the slotted inlet and also for tangential blowing Finally, an optimum inlet diffuser velocity distribution is developed (Author) A82-40925 " # A unique flight test facility - Description and results. R R Meyer, Jr (NASA, Flight Research Center, Edwards, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 433-448 13 refs The Dryden Flight Research Facility has developed a unique research facility for conducting aerodynamic and fluid mechanics experiments in flight A low aspect ratio fin, referred to as the flight test fixture (FTP), is mounted on the underside of the fuselage of an F-104G aircraft The F-104/FTF facility is de- scribed, and the capabilities are discussed The capabilities include (1) a large Mach number envelope (0 4 to 2 0), including the region through Mach 1 0, (2) the potential ability to test articles larger than those that can be tested in wind tunnels, (3) the large chord Reynolds number envelope (greater than 40 million), and (4) the ability to define small increments in friction drag between two test surfaces Data are presented from experiments that demonstrate some of the capabilities of the FTF, including the shuttle thermal protection system airload tests, instrument development, and base drag studies Proposed skin friction experiments and instrument evaluation studies are also discussed (Author) A82-40928 * # Determination of airplane aerodynamic parameters from flight data at high angles of attack. V Klein (Joint Institute for Advance- ment of Flight Sciences, Hampton, VA) and J G Batterson (NASA. Langley Research Center, Hampton, VA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics. 1982. p 467-474 8 refs The problem of determining airplane aerodynamic model equations and es- timating the associated parameters from flight data taken at high angles of attack is addressed Two representations of the aerodynamic function based on the polynomial and spline representations are given Then the technique of building an adequate model using a stepwise regression is presented with examples demonstrating the construction of the model and various approaches to model verification (Author) A82-40930 * # Computational and experimental studies of light twin aerodynamic interference. W G Thomson. W H Wentz, Jr, and C Ostowan (Wichita State University, Wichita, KS) In International Council of the Aeronauti- cal Sciences, Congress. 13th and AIAA Aircraft Systems and Technology Con- ference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1,(A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics. 1982. p 489-495 Research supported by the Beech Aircraft Co and NASA The results of an analytical and experimental study of aerodynamic interfer- ence effects for a light twin aircraft are presented Both the influence of a body (either fuselage or nacelle) on a wing and the influence of a wing on a body are studied The wing studied uses a new natural laminar flow airfoil with variable camber movable trailing edge A three-dimensional panel method program utiliz- ing surface source and surface doublet singularities was used to design wing- nacelle and wing-fuselage fairings Experiments were conducted using a 1 /6 scale reflection plane model Forces, pressures, and surface flow visualization results are presented Results indicate that potential flow analysis is useful to guide the design of intersection fairings, but experimental tuning is still required While the study specifically addressed a light twin aircraft, the methods are applicable to a wide variety of aircraft (Author) A82-40931 * # Dual wing, swept forward swept rearward wing, and sin- gle wing design optimization for high performance business airplanes. M D Rhodes and B P Selberg (Missoun-Rolla. University, Rolla, MO) In Interna- tional Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Pro- ceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 496-511 32 refs Grant No NAG1-26 An investigation was performed to compare closely coupled dual wing and swept forward swept rearward wing aircraft to corresponding single wing base- line' designs to judge the advantages offered by aircraft designed with multiple wing systems The optimum multiple wing geometry used on the multiple wing designs was determined in an analytic study which investigated the two- and three-dimensional aerodynamic behavior of a wide range of multiple wing con- figurations in order to find the wing geometry that created the minimum cruise drag This analysis used a multi-element mviscid vortex panel program coupled to a momentum integral boundary layer analysis program to account for the aerodynamic coupling between the wings and to provide the two-dimensional aerodynamic data, which was then used as input for a three-dimensional vortex lattice program, which calculated the three-dimensional aerodynamic data The low drag of the multiple wing configurations is due to a combination of two dimensional drag reductions, tailoring the three dimensional drag for the swept forward swept rearward design, and the structural advantages of the two wings that because of the structural connections permitted higher aspect ratios (Author) A82-40932 * # Assessment of advanced technologies for high per- formance single-engine business airplanes. D L Kohlman (Kohlman Aviation Corp, Lawrence, KS) and B J Holmes (NASA, Langley Research Center. Hampton, VA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, Au- gust 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, Ameri- can Institute of Aeronautics and Astronautics, 1982, p 512-563 24 refs The prospects for significantly increasing the fuel efficiency and mission capa- bility of single engine business aircraft through the incorporation of advanced propulsion, aerodynamics and materials technologies are explored It is found that turbine engines cannot match the fuel economy of the heavier rotary, diesel and advanced spark reciprocating engines The rotary engine yields the lightest and smallest aircraft for a given mission requirement, and also offers greater simplicity and a multifuel capability Great promise is also seen in the use of composite material primary structures in conjunction with laminar flow wing sur- faces, a pusher propeller and conventional wing-tail configuration This study was conducted with the General Aviation Synthesis Program, which can furnish the most accurate mission performance calculations yet obtained O C A82-40933 * # The design integration of wingtip devices for light gen- eral aviation aircraft. R V Gifford (NASA, Langley Research Center, Hampton, VA) and C P van Dam (Kansas, University, Lawrence, KS) In International Council of the Aeronautical Sciences. Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27. 1982, Proceedings 508 A82-40942 Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 564-569 21 refs An investigation was conducted to determine the load carrying capabilities and structural design requirements for wingtip devices on general aviation aircraft Winglets were designed and analyzed as part of a research program involving a typical agricultural aircraft This effort involved analytical load prediction for the winglets, structural design for both the winglets and aircraft installation, structural load testing and flight test verification Conclusions from this program are be- lieved to be applicable to the use of wingtip devices on light-weight general aviation aircraft (Author) A82-40934 # Operation V10F - Development of a composite material wing. G Hellard (Societg Nationale Industnelle Aerospatiale, Toulouse, France) and D Chaumette (Avions Marcel Dassault - Breguet Aviation, Vaucresson, Hauts-de-Seme, France) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA. August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 570-578 The design development and detailed structural and fabrication method fea- tures of the Falcon 10 business jet aircraft carbon fiber reinforced plastic com- posite wing are described, with emphasis on the design and testing of individual wing structure components such as stiffened ribs and integrally stiffened upper and lower surface panels The testing of laminate composite wing structure element properties included transverse loading, thermal and mechanical fatigue, shear, combined shear and bending, fuel pressure, tension, and compression The delamination and lightning strike behavior of the wing components were also assessed Finally, all structural elements were assembled and tested for static loads and fatigue The composite wing represents a 20 3 percent weight saving over the metallic wing it,replaces 0 C A82-40935 # A one-shot autoclave manufacturing process for car- bon epoxy components. M Kaitatzidis, R Renz (Dormer GmbH, Friednch- shafen, West Germany), and D Wurzel (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Stuttgart, West Germany) In Interna- tional Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Pro- ceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 579-585 For the Alpha-Jet aircraft Dormer has developed and fabricated a carbon- /epoxy horizontal stabilizer, which has already successfully completed its qualifi- cation tests This paper presents the requirements and goals of this development and describes the structural design of the horizontal stabilizer For its leading and trailing edges a new one-shot manufacturing technique has been developed The toolings are described, weight and cost savings are reported This technique is now being applied for series production of ailerons for the Do 228 Commuter Aircraft A brief presentation of the results of the qualification tests under various environmental conditions (humidity and temperature) is given (Author) A82-40936 # Non-honeycomb F-16 horizontal stabilizer structural de- sign. D N Butcher (General Dynamics Corp , Fort Worth, TX) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics. 1982, p 586-592 A description is given of the F-16 fighter's horizontal stabilizer structural design and fabrication methods The primary components of the stabilizer are gra- phite/epoxy composite skins, which are mechanically fastened with countersunk rivets to a one-piece sheet aluminum corrugated substructure and a machined aluminum pivot fitting The skins and substructure are tooled to a common inside mold-line surface to facilitate assembly Weight, construction and maintenance costs comparisons are made with the full depth-bonded honeycomb stabilizer design which the present one will replace Despite a weight of 1659 Ib, by comparison to 157 8, the new stabilizer represents a 50% fabrication cost reduc- tion at the 600th stabilizer produced Lower maintenance costs are expected, in view of the long-term service problems associated with the honeycomb fabrica- tion alternative O C A82-40937 # Material identification for the design of composite ro- tary wings. V Giavotto, C Caprile, M De Capitam, L Salviom (Milano] Politec- mco, Milan. Italy), V Caramaschi, G C Maffioli, and F Mussi (Costruzioni Aeronautiche Giovanni Agusta S p A , Gallarate, Italy) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 593-606 15 refs Among the developments that appear to be absolutely needed for the design of advanced composite rotary wings there are material models, to be supported by substantial experimentation and to be capable of an accurate modeling of the behavior of multilayer FRPs, complete of failure criteria regarding all possible failure modes This paper reports an experimental activity carried on by Aeros- pace Department of Politecnico of Milano in cooperation with Costruzioni Aeronautiche G Augusta The most relevant part of such activity has been a fairly large campaign on tubular specimens in biaxial stress states and plane speci- mens in umaxial stress states All tests have been run statically, measuring stresses and strains up to failure The results of such measurements have been so far worked out to verify existing material models and failure criteria No one existing failure criteria seems to be completely adequate to the whose stress domain explored (Author) A82-40939 # Dynamic energy transfer between wind and aircraft. G Schanzer (Braunschweig, Techmsche Universitat, Brunswick, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 615-621 6 refs The energy effect of vertical wind on glider aircraft is studied The theoretical basis of maximum dynamic energy transfer is discussed, and the energy transfer problem is investigated using a glider with up and downdrafts varying in space The response of the aircraft is calculated with a nonlinear simulation program on a digital computer Maneuvering that produces optimal energy transfer is con- nected with a high kinetic energy level of the aircraft and high load factors which depend on vertical wind velocities Energy-optimal flight maneuvers significantly increase the average groundspeed of a glider aircraft compared to the procedure described by Nickel and McCready (1949) C D A82-40940 # Digital computer simulation of modern aeronautical digital communication systems. S Chow (Nanjing Aeronautical Institute, Nanj- ing, People's Republic of China) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 622-629 11 refs A Monte Carlo simulation method for modern aeronautical digital communica- tion systems is described Its relationship to various parameters is studied, includ- ing filtering, limiting, carrier frequency offset, bit time jitter, and multipath effects in A/G and A/A communications (Author) A82-40941 # Flight simulation studies on the feasibility of laterally segmented approaches in an MLS environment. L J J Erkelens (Nationaal Lucht- en Ruimtevaartlaboratonum. Amsterdam, Netherlands) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference. Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 630-641 5 refs On the moving base flight simulator of the NLR an investigation was carried out to establish a number of minimum approach parameters concerning laterally segmented approach paths, assuming that guidance was provided by an MLS facility Seven laterally segmented approach paths with different turn angles and final intercept altitudes were flown manually with a simulated heavy transport aircraft in the final approach configuration Results were obtained in terms of tracking accuracy, pilot effort ratings and pilot responses to a questionnaire A subsequent simulation program was carried out recently, in which as new items were introduced a more realistic simulation of the MLS environment (MLS cover- age area and signal noise), implementation of aircraft configuration changes (flaps, landing gear) A third simulation program is prepared in which the interac- tion is emphasized between the air traffic controller and the flight crew The pilot is vectored to a point within MLS coverage, from which he is expected to intercept a laterally segmented approach path using MLS-guided intercept procedures (Author) A82-40942 # A concept for 4D-guidance of transport aircraft in the TMA. V Adam and W Lechner (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Brunswick, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982. Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 642-653 18 refs The four dimensional (4D) guidance of aircraft in the TMA allows for precise control of the minimum separation and thus efficient use of the available approach capacity of the airport A concept for the 4D-guidance of transport aircraft has been developed and a corresponding control mode has been integrated in an automatic flight control system for transport aircraft The 4D mode is based on the usual radar vector guidance technique of air traffic control and, therefore, is charactenzed by a succession of flight sections with constant values for indicated airspeed, heading and descent rate The time of arrival is controlled by altering the path via a delay fan The algorithm for the calculation of the commanded 4D flight path takes into account suitable wind models updated by actual wind data In the paper the 4D mode is described and first flight test results are discussed (Author) 509 A82-40943 A82-40943 # Optimal open-loop aircraft control for go-around ma- neuvers under wind shear influence. H G Jacob (Braunschweig, Techmsche Universitat, Brunswick, West Germany) In International Council of the Aeronauti- cal Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Con- ference. Seattle, WA, August 22-27. 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics 1982 p 654-664 24 refs The optimization procedure is based on the representation of time dependent command inputs by analytical functions The coefficients of these functions are iterated by a static search algorithm to values optimizing the behavior of the process The longitudinal motion in heavy tail wind shear of the Airbus A 300 aircraft is described by a system of nonlinear equations of 4th order bounded by numerous design, safety and comfort constraints The quality criterion is defined in a way to maximize the minimal distance between aircraft and ground as well as the area between flight path and ground For these studies a very simple optimization program has been used which allows to consider boundaries and which comprises less than 100 FORTRAN-statements The optimal input func- tions and other interesting variables are shown and discussed for the particular case that full power is available and for half power (Author) A82-40944 # The nonsynchronous whirls of the turbine rotor in aero- jet engines. J -L Gu and P -Z Ren (Northwestern Polytechmcal University, Xian, Shaanxi. People's Republic of China) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 665-673 12 refs Several factors involved in the stability analyses of the supercritical overhung- rotor-beanng system of a specific type of aircraft engine are discussed The phenomenon of 1 /2 order subharmonic vibration within aerojet engines and its causes are assessed, and mathematical expressions for destabilizing forces are worked out The latter include the unbalanced torque force due to circumferential variations of blade tip clearances, the frictional moment within splmed coupling, and the aeroelasticity of labyrinth seals Mathematical expressions for parametric excitation are found for the nonlinear stiffness of single-row deep-grooved ball bearings and for the nonlinear stiffness of the back support Equations of motion of the high-speed overhung turbine rotor are derived C D A82-40945 # Fluctuating forces and rotor noise due to distorted in- flow. G Neuwerth, R Staufenbiel, A Kellner, and J Schreier (Aachen, Rhei- nisch-Westfahsche Techmsche Hochschule,' Aachen, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 674-688 14 refs The influence of inflow distortions on the rotor blade forces and on their in- creased radiated noise is' theoretically and experimentally investigated Two types of distortions are considered, one involving a ducted rotor whose inflow is distorted by wakes, the other involving a helicopter tail rotor cutting the tip vor- tices of the mam rotor Fluctuations in the direction and magnitude of the flow relative to the blades is Fourier analyzed and the unsteady blade forces and pressures are computed on the basis of two and three-dimensional theories The Fourier coefficients of these forces are used to compute the additional rotor noise emission due to the inflow distortions Measurements of the unsteady blade pressures and the radiated noise power spectrum are in reasonable agreement with the theoretical results C D A82-40946 # An experimental and numerical study of 3-D rotor wakes in hovering flight. M Nsi Mba, D Favier, and C Maresca (Aix-Marseille I, Umversite, Marseille, France) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 689-699 12 refs Direction des Recherches, Etudes et Techniques Contract No 78-456 Results of comparison between experimental and numerical studies on the 3-D wake of a hovenng rotor are presented The wind-tunnel investigation is con- ducted by means of X-hot wires and laser Doppler anemometry procedures to measure the 3-D velocity field under the rotor and to determine the tip vortex paths for several rotor configurations Additional flow visualizations and rotor airloads coefficients are also carried out The prediction model is based on the classical vortex theory with an empirically prescribed geometry of the wake From the blade circulation distribution the rotor wake is represented by vortex lines which are allowed to freely adapt until a converged wake geometry is obtained Then a new estimate of the blade circulation repartition can be de- duced The procedure is repeated, iterating until the compatibility between the adapted wake geometry and the blade circulation repartition is obtained The validity range of the calculation model is deduced from comparison with experi- mental data obtained on instantaneous velocities and tip vortex paths, for dif- ferent rotor parameters including solidy, number of blades, pitch angle, blade twist, and tip shape (Author) A82-40947 * # Aerodynamic interactions between a 1/6-scale heli- copter rotor and a body of revolution. M D Betzina (NASA, Ames Research Center, Moffett Field, CA) and P Shmoda (U S Army, Aeromechanics Labora- tory, Moffett Field, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 700-711 6 refs A wind-tunnel investigation was conducted in which independent, steady-state aerodynamic forces and moments were measured on a 2 24-m-diam, two-bladed helicopter rotor and a body of revolution The objective was to determine the interaction of the body on the rotor performance and the effect of the rotor on the body aerodynamics for variations in velocity, thrust, tip-path-plane angle of attack, rotor/body position, and body nose geometry Results show that a body of revolution near the rotor can produce significant favorable or unfavorable effects on rotor performance, depending on the operating condition Body lon- gitudinal aerodynamic characteristics are significantly modified by the presence of an operating rotor and hub (Author) A82-40948 # The prediction of propeller/wing interaction effects. A S Aljabri (Lockheed-Georgia Co , Marietta, GA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 712-719 An analytical technique has been developed which predicts the influence of a propeller slipstream on a nacelle/wing combination This is achieved by coupling a slipstream code with a complex configuration potential flow analysis code The slipstream code is based on the vortex theory of propellers and predicts the slipstream in terms of its shape induced velocities and swirl angle To verify the slipstream code two experiments with different model propellers were carried out The wake immediately behind these propellers was surveyed and results compared with predictions Good correlation is obtained The coupling of the slipstream code with the panel code allows analysis of propeller slipstream/- nacelle/wmg combinations Results comparing the wing spanwise loading with and without slipstream are presented The computational results are found to be in good agreement with experimental data (Author) A82-40949 # Wind-tunnel testing of V/STOL configurations at high lift. W R Sears (Arizona, University, Tucson, AZ) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics. 1982, p 720-730 12 refs Contract No N00014-79-C-0010 The results of a study of the problem of the large airstream deflections involved in wind-tunnel testing of V/STOL configurations are reported The concept of adaptive wind-tunnel walls is utilized to eliminate, along with boundary interfer- ence, the inaccuracies of the usual tunnel calibration Some numerical models of adaptive-wall tunnels are described and it is shown that the undisturbed stream direction and magnitude, arbitrarily chosen, are achieved by the iterative process of such a tunnel The use of this type of tunnel in an extreme case is demonstrated by constructing and model testing an approximate panel representation of a jet-flap wing of finite span The demonstration is completely sucessful, suggesting that the new tunnel would solve the recurring problem of V/STOL testing C D A82-40950 # Estimation of simulation errors in the European Tran- sonic Wind Tunnel /ETW/. B Wagner (Dormer GmbH, Friednchshafen, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle. WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 731-740 22 refs Bundesmims- terium fur Forschung und Technologie Contract No LVW-7901, European Tran- sonic Wind Tunnel Contract No 79/01/68730/143963 Simulation errors in cryogenic wind tunnels caused by real gas effects, changes in viscosity and heat conductivity characteristics at low temperatures, heat transfer, and local condensation are estimated theoretically For this pur- pose viscous effects and heat transfer influences in transonic high Reynolds number turbulent flows are calculated by solving numerically the full Navier- Stokes equations for shock wave boundary layer interactions and by calculating boundary layers on airfoils, real gas equations of state and non-adiabatic walls being included in both procedures Equilibrium condensation approximating the case of heterogeneous nucleation is investigated in transonic airfoil flows by means of numerical solutions of the full inviscid Euler equations The separation behavior is shown not to be sensitive to real gas effects and small amounts of heat transfer The condensation influence is primarily seen by a considerable drag increase (Author) A82-40953 # Prediction of high alpha flight characteristics utilizing rotary balance data. W Bihrle, Jr (Bihrle Applied Research, Inc , Jericho, NY) In International Council of the Aeronautical Sciences. Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27.1982, 510 A82-40964 Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics. 1982, p 761-768 Rotational flow aerodynamic data, as measured by a rotary balance at low Reynolds number, are used to analytically predict steady spin modes and post- stall motions The excellent agreement obtained between predicted and full-scale flight results would indicate that use of low Reynolds number rotary balance data is sufficient for calculating steady-spin modes for military configurations and general aviation configurations not having large wing leading-edge radii Consid- erations, however, in the application of these low Reynolds number data to steady-state spin analysis, as well as large angle, six degree-of-freedom high alpha studies, are discussed Also, the procedure for developing a configuration highly resistant to spins is illustrated (Author) A82-40955 # Experimental and theoretical studies of three-dimen- sional turbulent boundary layers on an empennage of a typical transport airplane. H C Seetharam, N J Pfeiffer, M Ohmura, and J D McLean (Boeing Commercial Airplane Co , Seattle, WA) In International Council of the Aeronauti- cal Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Con- ference, Seattle, WA, August 22-27, 1982, Proceedings Volume 1 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 784-795 6 refs This paper describes experiments conducted to measure the three-dimen- sional incompressible turbulent boundary layers on the horizontal and vertical tails of a 1 /5 scale model of a transport airplane empennage The boundary layer measurements were made with a V-shaped anemometer with a high precision traversing mechanism Variations of angle of attack and Reynolds number were included in the tests Measurements were also made with small elevator and rudder deflections The data includes extensive pressure distributions, and de- tailed analyses of three-dimensional boundary layer data Comparison of the experimental data with a three-dimensional boundary layer code taking into ac- count viscous-mviscid interaction is shown Details of the test theory comparison and the need for a better turbulence model are discussed (Author) A82-40956 # Requirements and trends in fuel consumption in trans- port mission with aircraft and surface vehicles. G Gabnelli In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982. p 796-799 A discussion is presented of the energy utilization factor, f, which relates the payload product of a vehicle, yielded by weight and route distance, to the me- chanical energy used Values of f are presented which have been derived from several hundred sea, land and air vehicles of 15 different types in view of their customary missions It is demonstrated that turboprop aircraft, and to an even greater degree turbojet aircraft, are the only types of vehicles which offer higher transport speeds without a corresponding reduction in the energy utilization fac- tor OC A82-40957 # Aerodynamic concepts for fuel-efficient transport air- craft. G Krenz and R Hilbig (Veremigte Flugtechnische Werke GmbH, Bremen, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, Au- gust 22-27,1982, Proceedings Volume 2 (A82-40876 20-01) New York, Ameri- can Institute of Aeronautics and Astronautics, 1982, p 800-810 8 refs The rapid inflation of |et fuel prices in the last decade contributes largely to the growing operating expenses of the airlines and to a disproportionate share of the Direct Operating Costs (D O C ) as well, wherein the fuel share is already domi- nant This report describes the influence of the increasing fuel costs on the aircraft design and explains the manner in which the lift/drag ratio as design parameter is steadily increasing in importance compared to the weight The evaluation of the fundamentals for a new fuel efficient aircraft is a challenge for both, designer and aeronautical research On the other hand there still exist potentials for perform- ance improvements in terms of L/D for most of the current aircraft in service, as they were generally designed for minimum weight performance This paper gives examples for aircraft modifications for performance improvement and shows potentials for future designs in the field of aerodynamics (Author) A82-40959 # Cracks interacting with contact forces - A finite element study on loaded holes. H Ansell and B Frednksson (Saab-Scania AB, Lmkop- ing, Sweden) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, Au- gust 22-27,1982, Proceedings Volume 2 (A82-40876 20-01) New York, Ameri- can Institute of Aeronautics and Astronautics, 1982, p 818-825 17 refs Research supported by the Forsvaret Matenelverk A computerized method for the simultaneous solution of the contact and stress intensity factor problem has been developed The solution is based upon the finite element method using virtual crack extension method for stress intensity factor calculations The method is generally applicable to both two- and three-dimen- sional problems and both through- and part-through cracks could be studied The method has been applied to a lug with pressfitted sleeve and shaft. Both smgle- and doublesided cracks are studied Contact pressures and stress intensity fac- tors during crack propagating are presented The stress intensity factors are compared with experimental results The importance of the simultaneous solution of the contact and crack problem is demonstrated (Author) A82-40961 # A crack growth model under spectrum loading. B -X Yang (Beijing Institute of Aeronautics and Astronautics, Beijing, People's Republic of China) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 837-843 12 refs In the present study, based on the mechanisms of delayed retardation of overload retardation effect, an analytical equation for predicting the delayed retardation parameter is presented Further, a model for predicting the retarda- tion under tensile overloads and tensile-compressive overloads is proposed, and it can be used to predict the fatigue crack growth rate and fatigue life under complex spectrum loading And as an example, the retardation effects of some materials under different loading conditions are predicted The fatigue life of stiffened panel of wing and landing gear of aircraft under complex spectrum loadings are predicted Predictions agree very well with experimental results (Author) A82-40962 # Age exploration in naval aviation. A D Williams (U S Navy, Naval Aviation Logistics Center, Patuxent River, MD) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York. American Institute of Aeronautics and Astronautics, 1982, p 844-850 In this paper, an overview of the United States Navy's newly developed aviation age exploration process is given As age exploration is a subset of the Reliability- Centered Maintenance (RCM) program, the underlying concepts of age explora- tion, RCM, and their relationship to each other, are explored Age exploration is depicted as a multi-faceted analyzation, marrying diverse types of information with maintenance engineering logic and statistical formulation Specific applica- tions of the age exploration process, in the Navy's aviation community are presented It is shown how the knowledge gained from age exploration enables the designer of the RCM requirements to effect maximum uptime of the equip- ment at the lowest cost within the bounds of safety (Author) A82-40963 # Logistics research program in the United States Air Force. J C Reynolds and P E Davidson (USAF, Coordinating Office for Logis- tics Research, Wright-Patterson AFB, OH) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 851-853 An assessment is given of the factors which contribute to the lack of interest and investment of resources in logistics research and development, with empha- sis on the need to integrate the consideration of logistics into research and development activities, and attention to the program developed toward that end by the U S Air Force USAF program results demonstrate that any agency with logistics responsibilities can improve its technical capabilities and operational methods through management attention and the cooperation of the logistics and research and development communities O C A82-40958 # Progress at Douglas on laminar flow control applied to commercial transport aircraft. W E Pearce (Douglas Aircraft Co , Long Beach, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, Au- gust 22-27,1982, Proceedings Volume 2 (A82-40876 20-01) New York, Ameri- can Institute of Aeronautics and Astronautics, 1982, p 811-817 Design studies, development efforts and testing related to laminar flow control for subsonic commercial transport aircraft are described in this paper The paper covers selection of a suitable suction surface, integration of the suction system, and results of LFC aircraft design studies Current programs which include wind tunnel testing and flight testing are discussed as well as proposed future LFC activities (Author) A82-40964 # Third generation turbo fans. J F Coplm (Rolls-Royce, Ltd, Derby, England) In International Council of the Aeronautical Sciences, Congress. 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 867-878 The modular design concept of the RB211 family of turbofan aircraft engines has allowed the progressive improvement of fuel efficiency through refinement of the design of individual components, resulting in gradual increases of optimum pressure and bypass and temperature ratios The RB211-535E4, which is the latest engine derived from the basic RB211 design and is destined for use by the 757 airliner, incorporates inherent precision tip clearance control, thermal barrier coatings, creep-resistant" titanium alloys, supercritical airfoil designs, a single 511 A82-40965 nozzle exhaust, a single stage, wide chord clapperless fan, and three-dimen- sional core compressor and core turbine designs Attention is given to the basic research conducted on component efficiency, which involved the use of laser holography and laser anemometry techniques for observing and measuring aero- dynamic flow O C A82-4096S # Turboprop design - Now and the future. B S Gatzen (United Technologies Corp, Hamilton Standard Div. Windsor Locks, CT) In International Council of the Aeronautical Sciences, Congress. 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 879-903 92 refs After an account of the development history of turboprop rotor technology during the 1960s for V/STOL applications, the development status and design and performance characteristics of commuter aircraft turboprop and high speed propeller fan rotor technologies are considered The commuter aircraft propeller family incorporates composite shell and aluminum spar blades with a double- acting pitch change system and a pitch-lock feature, resulting in weight reduction, greater safety, improved durability, and a near-ideal aerodynamic performance in the Mach 0 4-0 65 range that assures low cabin noise levels and meets far field noise certification requirements The propeller fan incorporates 8-10 blades with swept blade tips for the Mach 0 65-0 8 range cruise speeds of 80-160 passenger transports and military cargo and ASW aircraft The propeller fan will result in fuel consumption reductions of 20% and 40% for commercial and military aircraft, respectively O C A82-40966 # Inflated wings. A Roselli In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 904-910 The design principles and possible uses of both statically and dynamically inflated wings are considered, on the basis of their inherently high strength/weight ratios, economy of construction, and ease of storage and deployment It is noted that the upper surface of a large statically inflated wing acts as a greenhouse- effect solar trap which may be harnessed to provide both static buoyancy, as in a hot air balloon, and energy for propulsion Attractive uses of these large, kite-like wings include auxiliary power for ships, seed, fertilizer and insecticide- spraying platforms for agriculture, and military parachutes O C A82-40967 # Design and tests of airfoils for sailplanes with an ap- plication to the ASW-19B. L M M Boermans and H J W Selen (Delft, Tech- nische Hogeschool, Delft, Netherlands) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 911-921 14 refs The paper describes the considerations, tests and results of an investigation aimed at designing some improved airfoils for sailplane applications The follow- ing preliminary studies are discussed Wmdtunnel experiments on two actual wing segments of a Standard Class sailplane ASW-19B are described The character- istics of some modern airfoils for sailplanes are analyzed Results of flight and wmdtunnel experiments with respect to leading edge contamination by insects are presented The effectiveness of pneumatic turbulators, applied to decrease the airfoil drag by avoiding laminar separation bubbles, is demonstrated Based on the experience gained in these studies, some airfoils were designed and. after wmdtunnel verification, applied to the wing of an ASW-19B Flight performance measurements before and after the wing modification showed an improvement of 5% in glide ratio over the entire practical flight speed range (Author) A82-40968 # Variable geometry aerofoils as applied to the Beatty B-5 and B-6 sailplanes. R A Streather (Atlas Aircraft Corp , Johannesburg, Repub- lic of South Africa) In International Council of the Aeronautical Sciences, Con- gress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 922-930 11 refs Two variable-geometry aerofoils using flexible surfaces have been developed by Beatty for his B-5 and B-6 sailplanes The B-5 has a basic Eppler 1001 section with a flexible upper surface which is raised to form a thick, high-camber profile for thermallmg The B-6 uses a Wortman FX 05-H-126 section with flexible upper and lower surfaces over the rear 40% of the chord Predictions for the polars of the two sections using the, Eppler and NASA viscous, two-dimensional computer programs are presented Predictions for the overall aircraft polars are compared with flight-test measurements obtained by conventional methods and by using a prototype glide-angle indicator (Author) A82-40969 # Development of the Circulation Control Wing-Upper Surface Blowing powered-hft system for STOL aircraft. M J Harris, J H Nichols, Jr, R J Englar, and G G Huson (David W Taylor Naval Ship Research and Development Center, Bethesda, MD) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27. 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 931-939 10 refs The design characteristics and performance levels attained in static, wind tunnel and test aircraft operation of the Circulation Control Wing/Upper Surface Blowing (CCW/USB) powered lift system for STOL aircraft are described The configuration of the system places turbofan engine exhausts above the upper surface of a Coanda-effect trailing edge circulation-control wing, so that the exhaust gases scrub the wing upper surface In addition to controlling effective wing camber with circulation control blowing, propulsion-induced lift is generated through the downward deflection of turbofan exhaust over the trailing edge of the wing to a degree which is controlled pneumatically by the momentum of the circulation-control jet sheet It is experimentally demonstrated that the mechani- cally simple CCW/USB pneumatic system can generate high lift as effectively as the heavier and more complex mechanical flap systems O C A82-40970 # Ejector powered propulsion and high lift subsonic wing. R A Squyers, J L Porter (Vought Advanced Technology Center, Dallas, TX), K S Nagaraja (USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB, OH), and G F Cudahy (Fairchild Republic Co . Farmmgdale, NY) In Interna- tional Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Pro- ceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 940-950 8 refs Contract No F33615-79- C-3017 A high performance ejector wing is designed by means of methodologies based on three-dimensional vortex lattice and lifting line theories and two-dimensional analog techniques, in conjunction with viscous flow predictions and empirically based ejector augmentor design and performance procedures The initial analyti- cal consideration of various ejector wing configurations established the superior lift and thrust performance at high angles of attack of a configuration consisting of a constant pressure mixing elector with a wing lower surface inlet and an upper wing trailing edge exhaust flow Test results for a swept planform, four-ejector bay wing configuration indicate maximum lift/drag ratio improvements over a conventional wing of up to 27%, and an angle of attack increase of more than 10 deg without stall A thrust augmentation factor of 1 06 was achieved at a freestream Mach number of 0 294, in keeping with predictions O C A82-40971 # Development of an advanced no-moving-parts high-lift airfoil. R J Englar (David W Taylor Naval Ship Research and Development Center, Bethesda, MD) In International Council of the Aeronautical Sciences, CongressJ 3th and AIAA Aircraft Systems and Technology Conference, Seattle. "WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 951-959 15 refs An advanced Circulation Control Wing (CCW) airfoil has been developed by incorporating a very small radius blown trailing edge into the aft profile of an existing supercritical airfoil This combined no-moving-parts configuration gener- ates the same high lift as the already flight-proven large-radius CCW airfoils (section lift coefficient near 7), yet produces negligible unblown drag penalty due to leaving the device deployed for cruise flight The large leading edge radius of the supercritical airfoil allows high-lift operation without mechanical deflection Experimental results presented by the paper imply the feasibility of an efficient mono-element cruise and high-lift airfoil, with transition between the two modes accomplished by merely initiating blowing from the fixed trailing edge slot Com- parisons to existing blown and unblown high lift systems are made, and possible applications are discussed (Author) A82-40972 # Design integration of CCW/USB for a sea-based air- craft. H S D Yang (Lockheed-California Co , Burbank, CA) and J H Nichols. Jr (David W Taylor Naval Ship Research and Development Center. Bethesda. MD) In International Council of the Aeronautical Sciences. Congress. 13th and AIAA Aircraft Systems and Technology Conference. Seattle. WA. August 22-27. 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 960-968 8 refs A design study is being conducted to apply the technologies of Circulation Control Wing with Upper Surface Blowing (CCW/USB) engine installation to a Navy/Lockheed sea based aircraft Research and development in the CCW and USB concepts indicate that the application of the combined technologies may achieve a goal of operating the S-3 type aircraft from a ship deck without the catapult The design emphasizes the integration of the propulsion system with a simple installation to obtain high lift or drag when required Attention is also being directed to the cruise efficiency and the optimum design approach for stability and control (Author) A82-40973 # Aircraft design for fuel efficiency. L O Lehman. D Woll. and C Lampart (U S Naval Material Command. Naval Air Development Center Warmmster, PA) In International Council of the Aeronautical Sciences. Con- gress, 13th and AIAA Aircraft Systems and Technology Conference. Seattle WA August 22-27, 1982. Proceedings Volume 2 (A82-40876 20-01) New York American Institute of Aeronautics and Astronautics. 1982. p 969-979 6 refs U S Navy Aircraft Energy Conservation Research. Development Test and 512 A82-40984 Evaluation Program recommendations to date are presented, with emphasis on those aircraft design approaches which promise the greatest fuel savings for a given level of investment In addition to design modifications which reduce aero- dynamic drag or aircraft weight, attention is given to efficiency-enhancing propul- sion system concepts, Flight Performance Advisory/Management Systems which improve mission fuel utilization, and mission planning and training tech- niques which improve operational effectiveness The study results cover fighter, attack and patrol aircraft, and includes recommendations for such year 2000 air vehicles as nuclear aircraft and advanced lighter-than-air vehicles O C A82-40974 * # Performance characteristics of a buoyant quad-rotor research aircraft. B L Nagabhushan, P P Jacobs, C E Belknap (Goodyear Aerospace Corp , Defense Systems Div . Akron, OH), and D A Euler (Hughes Helicopters. Inc , Commercial Engineering Div . Culver City, CA) In International Council of the Aeronautical Sciences. Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 980-989 Contract No NAS2-10777 Performance characteristics of a buoyant, quadrotor research aircraft, which represents a hybrid airship concept for heavy lift application, are described Ceiling altitude and endurance for hovering at typical power levels, including partial power failure, are predicted Climb performance at various altitude and gross weight conditions have been examined Forward flight performance of this vehicle is illustrated in terms of typical performance parameters such as max- imum speed, maximum range, and endurance, over the full range of its payload capability Optimum payload weights have been identified which result in max- imum range at sea level density altitude and constant endurance at various altitudes, both during hover and cruise flights (Author) A82-40975 # Application of a new hybrid material/ARALL/in aircraft structures. J W Gunnink, L B Vogelesang, and J Schi|ve (Delft, Technische Hogeschool, Delft, Netherlands) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 990-1000 18 refs An aircraft structural material produced by the bonding of thin aluminum alloy sheets with an aramid fiber-reinforced adhesive, designated Aramid-Reinforced Aluminum Laminate (ARALL), is described ARALL exhibits superior fatigue crack growth properties, and has a high tensile strength which may be maximized through the introduction of suitable residual stresses into laminates havino opti- mized aluminum sheet thicknesses Monolithic material test results are used as reference in comparative tensile strength and fatigue tests for notched and cen- trally cracked ARALL specimens, bolted and riveted joints, and lugs Buckling test results are compared with calculations for both aluminum alloy and ARALL com- pression panels Attention is given to the weight savings obtainable in pressurized cabins representative of various existing aircraft through the use of ARALL OC A82-40976 # The behavior of composite thin-walled structures in dy- namic buckling under impact. J An-Gur, J Singer (Technion-lsrael Institute of Technology, Haifa, Israel), and H ROhrle (Dormer GmbH, Friednchshafen, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1001-1010 12 refs The influence of material properties, and in particular those of composites, on response and behavior of columns under axial impact is studied An extensive experimental investigation has been carried out on specimens made of gra- phite/epoxy, glass/epoxy and Kevlar/epoxy laminates with different layups Dy- namic buckling and failure are compared with those of metal columns and the relative advantages and disadvantages of the composite materials are discussed In general, composite columns show improved dynamic buckling properties, and, with several exceptions, they may replace metal ones efficiently and reliably (Author) A82-40977 # Nondestructive testing in aircraft construction using holographic methods. K Wanders (Deutsche Forschungs- und Versuchsan- stalt fur Luft- und Raumfahrt, Cologne, West Germany) and H Stembichler (Laboratory Dr H Stembichler, Endorf, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982. p 1011-1017 10 refs The application of high power laser-based holographic interferometry to air- craft structure nondestructive testing is described The techniques covered in- clude real time holography, which denotes structural deformation through the dark bands of destructive interference, the double exposure method, in which structural stresses applied between exposures are manifested as interference fringes among odd multiples of one-half wavelength, and time-average hologra- phy, which reconstructs wavefront interference between two virtual images of a vibrating structure The concrete examples given are of a glass fiber-reinforced plastic tube, a helicopter rotor blade, the running surface of a tire, a turbine rotor, and a thermally deformed antenna, as well as exhaust nozzle jets 0 C A82-40978 # Design and fabrication of cocured composite hat-stiff- ened panels. G D Peddie and E E Spier (General Dynamics Corp , Convair Div, San Diego, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 2 (A82-40876 20-01) New York. American Institute of Aeronautics and Astronautics, 1982, p 1018-1031 7 refs Design/analysis study established cocured graphite-epoxy hat-stiffened pan- els of high compressive structural integrity for development and demonstration by mechanized methods Both flat and curved-crown hats were involved in the design/analysis study, but only the flat-crown concept was included in the manu- facturing study It was found that manufacture of the curved-crown hat would not result in added complexity Post-buckling structural integrity was assumedjp be directly related to the summation of classical local bifurcation buckling strengths of panel elements Parts were built in stages with the final panel being 18 feet long Mechanization and tooling procedures were proven to be valid for the manufacturyof long panels Test panels were not fabricated in time for correlation with analysis, but testing will be performed in the near future (Author) A82-40979 # Spin behaviour of the Pilatus PC-7 Turbor Trainer. P Wittwer and O Masefield (Pilatus Flugzeugwerke AG. Stans, Switzerland) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1032-1039 Experience gained during the development of the PC-7 Turbo Trainer aircraft suggests that while spin tunnel tests are helpful in determining the critical points of a design's spin characteristics, an exhaustive and accurate forecast of spin behavior is not attainable The spin tunnel test model used for the PC-7 had a generally steeper nose-down attitude, and was faster turning, than the prototype aircraft Recovery turns were, however, accurately represented Attention is given to the differences in spin behavior resulting from a series of modifications to the prototype aircraft in the course of its spin test program O C A82-40982 # Models for the motor state of VSCF aircraft electrical power system. X Qiu.Y Yan.andY Hu (Nanjing Aeronautical Institute, Nanjing, People's Republic of China) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1061-1071 Mathematical models for the motor state of an AC-AC variable speed constant frequency (VSCF) power system are established in this paper Two computing methods, of which the first is a method for finding the analytic solution of the state transition matrix with a computer and the second is a combination of the 0 618- optimization method and the Runge-Kutta method, are proposed These methods reduce computation time (Author) A82-40983 # The effect of intake flow disturbances on APU compres- sor blade high cycle fatigue in the Airbus A300. K W Letter and J JOrg (Messerschmitt-BOIkow-Blohm GmbH, Munich, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1072-1081 7 refs Premature compressor failures of the APU in the Airbus A300, related to high cycle fatigue, led to a detailed investigation of the relevant intake/engine parame- ters Relatively high total pressure distortion and excessive flow angularity have been determined to be the cause of high alternating blade loads and, in combina- tion with the chosen material of the compressor disk and blades, surface fretting In systematic test steps intake modifications were developed to improve the intake flow quality It is shown that only relatively minor intake modifications were required to achieve a substantial improvement in total pressure distortion and swirl In addition, a suitable modification at the compressor blade dove-tails was initiated to increase trie blades' fatigue strength (Author) A82-40984 # Engine controls for the 1980s and 1990s. V A Fisher (Rolls-Royce, Ltd , Bristol, England) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle. WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982. p 1082-1087 After a brief developmental history of full-authority electronic engine control systems, with attention to that employed by the Olympus 593 engines of the Concorde SST. consideration is given to the developmental prospects for such systems in the near future in view of the increasing power of microprocessors 513 A82-40985 The fault tolerance characteristics, transducer systems, high integrity software and reliability/maintainability of the projected full authority digital electronic con- trol (FADEC) system are described, with attention to fault identification and flight crew notification procedures The RB211-535C turbofan engine will be equipped with such a FADEC system . O C A82-4098S # Advanced aerodynamic wing design for commercial transports - Review of a technology program in the Netherlands. N Voogt < (Fokker, Amsterdam, Netherlands) and J W Slooff (National Lucht- en Ruim- tevaartlaboratonum, Amsterdam, Netherlands) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 1088-1098 16 refs An aerodynamic technology development program is described, whose mam objectives are the formulation and validation of a computational procedure for the aerodynamic design of high aspect ratio wings for the transonic regime of short- /medium range commercial aircraft, as well as the establishment of a transonic technology base An inverse procedure has been formulated for the wing design task which allows the excerase of explicit control over wing geometry while approaching the target pressure distribution as closely as possible Experience has been gained in relating target pressure distributions to off-design conditions through two-dimensional airfoil and three-dimensional wing studies, together with wind tunnel verifications that included the assessment of high Reynolds number characteristics A wing-body configuration computational analysis capability for drag minimization studies has also been achieved by the program O C A82-40986 # Recent airfoil developments at DFVLfl. H Korner and G Redeker (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Institut fur Entwurfs-Aerodynamik, Brunswick, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27. 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1099-1114 37 refs New airfoils may bring a substantial improvement in the aerodynamic efficiency of airborne vehicles A number of new airfoils based on transonic and laminar concept have been designed and investigated at DFVLR With theoretical design methods and facilities for experimental verification at hand, airfoils for subsonic transports, sail-planes, propellers, helicopter rotors and combat aircraft have been developed (Author) A82-40987 # Wing-tip jets aerodynamic performance. J M Wu, A Vakih, and Z. L Chen (Tennessee, University, Tullahoma, TN) In. In- ternational Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2. (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1115-1121 32 refs. Contract No F33615-81-K-3034 This paper presents the preliminary study of wing-tip jets blowing techniques to achieve improvements in the wings aerodynamics per- formance The feasibility of utilizing wing-tip jets to reduce the currently popular wmglets has been conducted The idea is to study the potential of replacing solid wmglets by more flexible wing-tip jets to suit changing flight conditions The wing-tip jets modify the flow-field near the wing tip and could achieve better aerodynamic performance of the wing A first order calculation has been made to check the air-jet advantage versus the disadvantage in degrading the jet-engine performance by bleed-off of compressed air The result indicate that the power (or thrust) saved is significant enough to encourage us to explore this new concept Munk's minimum induced drag criterion has been extended to formulate the split branched wing-tips by utilizing multi-ports jet Moreover, it is also con- ceived that an added jet swirling effect may induce a circulatory motion. The induced local downwash could alter the new wing-tip flow and thus suppress the main wing-tip-roll-up vortex For this purpose, wind-tunnel tests with a half-wing model have been conducted to verify this concept This is done by controlling the jet blowing direction and magnitude (Author) A82-40988 # An experimental investigation of leading-edge span- wise blowing. W Su, M Liu, B Zhou, C Qiu, and S Xiong (Beijing Institute of Aeronautics and Astronautics, Beijing, People's Republic of China) In Interna- tional Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Pro- ceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1122-1132 13 refs Oil flow visualizations and pressure measurements on a 30-deg swept trapezoidal wing were conducted to investigate leading edge spanwise blowing. (LE SWB), which is very near the leading edge and along it The LE SWB can provide a higher maximum lift coefficient than conventional SWB It can generate a more stable jet leading edge vortex above the inboard wing, and the outboard wing leading edge vortex can also be enhanced The flow patterns of the wing with LE SWB are similar to those of a strake-wmg configuration (Author) A82-40989 # Vortex formation over double-delta wings. U Brennen- stuhl and D Hummel (Braunschweig, Technische Univenstat, Brunswick, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1133-1146 20 refs Low speed wind tunnel tests have been carried out on a series of double-delta wings The effects of variations in leading edge kink angle and in kink position have been investigated by mens of three-component pressure distribution and flow-field measurements, as well as by flow visualization at a Reynolds number value of 1 3 million At small angles of attack two primary vortices exist on each side of the wing, originating from the apex and from the leadmg-edge'kmk At moderate kink angles these two vortices join each other with increasing angle of attack The junction process is analysed in detail and is mtrepreted as a 'potential flow effect' At very large angles of attack vortex breakdown occurs within the jointed vortices, which leads to the limitation of the aerodynamic coefficients (Author) AS2-40990 # CATIA - A computer aided design and manufacturing tridimensional system. F Bernard (Avions Marcel Dassault-Breguet Aviation, Suresnes, Hauts-de-Seme, France) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1147-1154 A propenetary computer graphics-aided, three-dimensional interactive applica- tion (CATIA) design system is described CATIA employs approximately 100 graphics displays, which are used by some 500 persons engaged in the definition of aircraft structures, structural strength analyses, the kinematic analysis of mo- bile elements, aerodynamic calculations, the choice of tooling in the machining of aircraft elements, and the programming of robotics CATIA covers these diverse fields with a single data base After a description of salient aspects of the system's hardware and software, graphics examples are given of the definition of curves, surfaces, complex volumes, and analytical tasks O C A82-40991 # CDS-the designer's media, the analyst's model. D P Raymer (Rockwell International Corp, Los Angeles, CA) and S K Albrecht (Rockwell International Corp , Space Transportation and Systems Group, Dow- ney, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York. American Institute of Aeronautics and Astronautics, 1982, p 1155-1163 6 refs A proprietary Configuration Development System (CDS) is described which incorporates both a flexible interactive graphics program for the conceptual de- sign of aerospace vehicles and a three-dimensional geometric data base which may be used by analysis programs Experience to date with the CDS has demon- strated substantial productivity improvements, although, as noted by Sandusky' (1978), such gams are more pronounced in the conduct of iteration procedures than in the reduction of throughtime Nevertheless, optimal results are reached at an earlier stage of the design process Graphics examples are given from CDS work on the FDL-5 and FDL-8 lifting body manned orbital vehicles O C A82-40992 * # Aircraft geometry verification with enhanced computer- generated displays. J V Cozzolongo (NASA, Ames Research Center, Moffett Field, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1163/a-1163/j 11 refs A method for visual verification of aerodynamic geometries using computer- generated, color-shaded images is described The mathematical models repre- senting aircraft geometries are created for use in theoretical aerodynamic analyses and in computer-aided manufacturing The aerodynamic shapes are defined using parametric bi-cubic splmed patches This mathematical representa- tion is then used as input to an algorithm that generates a color-shaded image of the geometry A discussion of the techniques used in the mathematical repre- sentation of the geometry and in the rendering of the color-shaded display is presented The results include examples of color-shaded displays, which are contrasted with wire-frame-type displays The examples also show the use of mapped surface pressures in terms of color-shaded images of V/STOL fighter- /attack aircraft and advanced turboprop aircraft (Author) A82-40993 # Technical and economic comparison of carbon fiber tape and woven fabric applications. G Hilaire and G Briens (Societe Na- tionale Industnelle Aerospatiale, Laboratoire Central, Suresnes, Hauts-de-Seme, France) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1164-1172 A comparative study is made of the structural performance characteristics of various types of carbon fiber fabrics and unidirectional filament prepreg tapes, in view of the relative equality of the importance, in recent applications of carbon 514 A82-41003 fiber composites, of weight reduction, strength maximization, and reductions in manufacturing costs The comparisons are between a 3000-filament (3 K) tow, T 300 carbon fiber, 5 H satin weave cloth weighing 285 g/sq m when dry, and a 3 K T 300 tape Both are impregnated with 5208 resin and in that state represent 60 percent fiber volume composites The performance charactersitics considered are interlammar shear, notched and unnotched tensile strength, and compressive strength The consequences of each alternative for manufacturing are assessed for the cases of manual and automated lay-up, machining and cut trimming OC A82-40994 # Application of composite materials and new design concepts for future transport aircraft. R H Lange and J W Moore (Lock- heed-Georgia Co, Marietta, GA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1173-1181 30 refs The application of advanced technologies and the use of innovative aircraft design concepts show the potential for significant improvement in the fuel effi- ciency of future transport aircraft envisioned for operation in the mid to late- 1990s This paper reviews recent preliminary design system studies of transport aircraft featuring cost/benefit analyses of advanced technology and new vehicle design Concepts Emphasis is directed toward the use of graphite epoxy compos- ite materials in the primary and secondary structures of transport aircraft The data on aircraft design concepts include preliminary design studies of Advanced Civil/Military Aircraft (ACMA) aircraft and innovative configurations The aircraft design parameters include cruise Mach numbers of 0 75 to 0 80, design payloads from 330,000 to 772,000 Ibs, and range from 3,500 to 4,000 nautical miles (Author) A82-40<)95 # Sliced disc design - A composite conform concept for a turbo engine axial compressor. R Kochendorfer (Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt, Institut fur Bauweisen- und Konstruk- tionsforschung, Stuttgart, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics. 1982, p 1182-1191 5 refs For an 800 kW turbo engine demonstrator an axial compressor concept in composite technology was developed The aim was a reduction of mass and moment of inertia compared to a titanium design The geometry and the blade spacing required a single-blade attachment concept To minimize the problems in the shear loading area, the 'compressor rotor' was divided into individual segments, made of aluminum alloy Each of the Al-segments represents the root part of a B/AI blade In the leading and trailing edge areas these segments are shrunk together by composite hoops, which also sustain the centrifugal loads As long as the shrinkage pressure is present, the segmented disk exhibits a similar behavior as an unshced disk This sliced disk concept was successfully proof- tested in cold spin tests up to the design level of 47,600 rpm, corresponding to a maximum blade tip speed of 420 m/sec (Author) A82-40996 # Comparison of HP turbine 'deep blade design' effects in turbofan engine gas generators with different bearing structure configura- tions, ro Rist (Munchen, Technische Universitat, Munich, West Germany) In International Council of the Aeronautical Sciences. Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27,1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1192-1202 5 refs Two different types of gas generator bearing structure configurations have been investigated for a projected turbofan engine based on the deep blade design concept Mechanical analyses are carried out for defined operation and load cases to estimate the required mass increase for the main components It is shown that when the HP turbine rotor blade chord length is increased by 50%, the mass of the turbofan engine core increases by about 7 and 11 % for the two configurations investigated V L A82-40998 # Redundant control unit for an advanced multispool en- gine. G Oahl (Bodenseewerk Geratetechmk GmbH, Uberlmgen, West Ger- many) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1214-1221 The advantages and disadvantages of the use of digital technology for the control of modern multispool engines are discussed with reference to a newly developed redundant digital engine control unit The controller structure is dis- cussed with emphasis on software design and software verification methods It is shown that the many advantages resulting from the introduction of digital technology, such as increased reliability, improved maintainability, and internal controller intelligence, make up for the inevitable disadvantages associated with the sampling process and computer delay time V L A82-40999 # Test results of chordwise and spanwise blowing for low-speed lift augmentation. G A Howell (General Dynamics Corp, Fort Worth, TX) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1222-1234 11 refs Low-speed wind tunnel tests were conducted on a large-scale and a small- scale powered model of a STOL wing/canard concept with engines mounted over the wing In a basic configuration, both models exhausted the entire nozzle- flow momentum over vectoring flaps In an alternate configuration, both models exhausted a portion of the flow from spanwise nozzles in the outer nacelle wall to obtain wmg-leading-edge vortex augmentation Force and pressure data were obtained for the small-scale model powered by compressed air Pressure and thermal data were obtained for the large-scale model powered by two turbojet tengmes Chordwise blowing decreased the pressures over the entire wing upper surface and even on the canard at high angles of attack The power-induced lift coefficients were moderate for chordwise blowing Spanwise blowing increased the strength of the wing leading-edge vortex and reduced the pressure on the wing upper surface beneath the path of the vortex (Author) A82-41000 # Aerodynamic research applications at Boeing. A L Na- gel (Boeing Commercial Airplane Co , Seattle, WA) In International Council of the Aeronautical Sciences, Congress. 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle. WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 1235-1242 24 refs This paper shows by several recent examples how aerodynamic research tools and methods have been applied to the design of subsonic commercial transport airplanes Examples include wing modifications, nacelle integration, vortex gener- ators, and cab design Some recent high Reynolds number tests in the NASA 0 3-meter Transonic Cryogenic Tunnel are also described (Author) A82-41001 # Wind tunnel test and aerodynamic analysis of three aeroelastically tailored wings. W W Braymen.W A Rogers (General Dynam- ics Corp , Fort Worth, TX), and M H Shirk (USAF, Flight Dynamics Laboratory, Wright-Patterson AFB, OH) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1243-1255 11 refs USAF-sponsored research Aeroelastic tailoring of composite lifting surfaces was validated in a program that involved design, fabrication, and transonic wind tunnel testing of three stat"- aeroelastic wings in addition to a set of steel wings Each aeroelastic wing had unique design objectives The test featured aeroelastic shape documentation through the use of photogrammetry along with the simultaneous acquisition-of forces and pressures Highlights of the aerodynamic test results are presented, with emphasis placed on test-to-theory comparisons The strong' points as well as areas of needed improvement in the aerodynamic design methods are dis- cussed The investigation demonstrates that the design of composite lifting sur- faces should include consideration of aerodynamic benefits available through tailoring (Author) A82-41002 * # Upper Vortex Flap - A versatile surface for highly swept wings. D M Rao (Vigyan Research Associates, Inc , Hampton, VA) In Interna- tional Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Pro- ceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1256-1266 9 refs NASA-supported re- search The Upper Vortex Flap (UVF) is a multipurpose surface concept to improve the subsonic aerodynamics of highly swept delta wings Hinged along the leading edges and deployed from the wing upper surface, the UVF generates a vortex inboard on the wing in addition to the leading-edge vortex acting on the flap The relative suction levels on the wing and on the flap surface, governed by the flap angle and angle of attack, lead to a variety of functional applications viz lift increment, drag modulation, lift/drag improvement and roll augmentation This paper presents wind tunnel force and pressure measurements on a 74-deg flat plate delta to define the UVF-related vortex effects and to assess its potential as a versatile control surface in different angle-of-attack regimes (Author) A82-41003 * # Analytical study of vortex flaps on highly swept delta wings. N T Fnnk (NASA, Langley Research Center, Hampton, VA) In Interna- tional Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Pro- ceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1267-1275 25 refs This paper highlights some current results from ongoing analytical studies of vortex flaps on highly swept delta wings A brief discussion of the vortex flow analysis tools is given along with comparisons of the theories to vortex flap force and pressure data Theoretical trends in surface pressure distribution for both angle-of-attack variation and flap deflection are correctly predicted by Free Vor- 515 A82-41004 tex Sheet theory Also shown are some interesting calculations for attached-flow and vortex-flow flap hinge moments that indicate flaps utilizing vortex flow may generate less hinge moment than attached flow flaps Finally, trailmg-edge flap effects on leading-edge flap thrust potential are investigated and theory-experi- ment comparisons made (Author) A82-41004 * # Wind-tunnel investigation of vortex flaps on a highly swept interceptor configuration. W E Schoonover, Jr (NASA, Langley Re- search Center, Hampton, VA) and W E Ohlson (Boeing Military Airplane Co , Seattle, WA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, Au- gust 22-27,1982, Proceedings Volume 2 (A82-40876 20-01) New York, Ameri- can Institute of Aeronautics and Astronautics, 1982, p 1276-1290 15 refs A subsonic wind-tunnel investigation of the application of vortex flaps to a supersonic interceptor configuration is described Experimental results are presented which indicate the aerodynamic effects of vortex-flap deflection, trail- mg-edge flap deflection, vortex flap chord and span, vertical stabilizers, and a highly cambered leading edge designed for attached flow Data presented in- clude longitudinal forces and moments, upper-surface pressure distributions, and oil- and smoke-flow visualization photographs It is concluded that a full-span deployable vortex flap can provide a substantial performance improvement for this and other similar configurations (Author) A82-41005 # Spanwise distribution of vortex drag and leading-edge suction in subsonic flow. S N Wagner (MOnchen, Hochschule der Bunde- swehr, Neubiberg, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1291-1301 12 refs The spanwise distribution of the leading-edge suction force of wings with arbi- trary planforms is calculated on the basis of a linear subsonic thin-wing theory and a study by Carlson and Mack (1980) on two-dimensional airfoil sections The approach makes it possible to account for the effects of Mach number, Reynolds number, and wing parameters, including local thickness to chord ratio, location of the maximum wing section thickness, local leading-edge radius, and leading- edge sweep Results obtained by the proposed method are found to be in good agreement with experimental data V L A82-41006 # Fuselage effects in leading edge vortex flap aerody- namics. J F Marchman, III and M L Hollms (Virginia Polytechnic Institute and State University, Blacksburg, VA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics. 1982, p 1302-1309 8 refs Wind tunnel tests were conducted to determine the influence of a fuselage on the aerodynamic behavior of a 60 deg delta wing with leading edge vortex flaps The results showed that at some combinations of angle of attack and yaw, the fuselage had a stabilizing effect on the leading edge vortices and that maximum lift is increased due to fuselage lift and added vortex stability The fuselage did not affect the ability of vortex flaps to significantly increase the L/D of the wings (Author) A82-41007 # New technology for the next generation of commercial transports - Real or imaginary. I S Macdonald In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 1310-1320 Economical, technical, financial, and legal implications associated with the needed replacement of technically and economically obsolete fleets of old com- mercial aircraft are examined The discussion includes a brief review of the factors necessitating changes in aircraft fleets, a review of what aircraft and engine manufacturers have done to respond to the needs of the airlines to upgrade their fleets, new developments which will make it possible to increase the safety, efficiency, and profitability of commercial aircraft, and possible deter- rents to the successful and useful implementation of new technology V L A82-41008 * # An initial look at the supersonic aerodynamics of twin- fuselage aircraft concepts. R M Wood, S M Dollyhigh, and D S Miller (NASA, Langley Research Center, Hampton, VA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference. Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 1320/3-1320/h 15 refs Results of two studies into the supersonic aerodynamics of twin-fuselage air- craft configurations are summarized In the first study, a set of experimental data was obtained on a simple rectangular-wing twin-fuselage wind-tunnel model, this data was then used to evaluate prediction methods, assess favorable interfer- ence effects, and identify any unexpected or unpredictable aerodynamic phenomena Results are presented which show that significant reductions in wave drag are possible through optimum body positioning and that existing aero- dynamic prediction methods are adequate for making preliminary aerodynamic estimates Several configuration concepts were theoretically explored in the sec- ond study, and results are presented which indicate the sensitivity of the twin- fuselage concept to various methods of integrating the aircraft components (Author) A82-41009 # Reduced nonlinear flight dynamic model of elastic structure aircraft. J Jankovic (Beograd, Univerzitet. Belgrade, Yugoslavia) In International Council of the Aeronautical Sciences. Congress. 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA. August 22-27, 1982. Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1321-1329 11 refs A flight dynamics model defined by equations of motion for the case of an unconstrained deformable body subjected to aerodynamic forces, thrust load and aircraft weight is presented, with a deformable structure represented by the finite element method A reducing method based on the small energy and large damp- ing characteristics of very fast modes is introduced which involves the determina- tion of the generalized coordinate nonlinear vector transformation which can turn the basic nonlinear model to a linear one The method of decoupling linear systems to subsystems of slow and fast models makes it possible to extract fast structural modes and find a linear dependence between generalized, transformed coordinates A criterion for neglecting these modes is also presented It is. finally, necessary to find the nonlinear dependence between basic generalized coordi- nates which leads to the reduced nonlinear model of the system O C A82-41010 # Determination of load spectra and their application for keeping the operational life proof of sporting airplanes. H J Kossira (Braunschweig, Technische Universitat, Brunswick, West Germany) In Interna- tional Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA. August 22-27, 1982, Pro- ceedings Volume 2 (A82-40876 20-01) New York. American Institute of Aeronautics and Astronautics, 1982. p 1330-1338 Modern load spectrum determination techniques are applied to glass fiber- reinforced plastic (GFRP) sailplanes, with attention to the estimation of aircraft structure service life The use of such methods in the case of sailplanes is demanded by their combined gust and maneuver load environments The prepa- ration of data gathered during a limited time interval by means of computers, using Markov transition matrix storage and extrapolation to the total lifetime of the sailplanes, is demonstrated O C A82-41011 # The role of the scale parameter in service load assess- ment and simulation. J Gedeon (Budapesti Muszaki Egyetem, Budapest, Hun- gary) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27. 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1339-1349 23 refs The integral scale L, which is a universal parameter for stationary stochastic processes and complementary to the standard deviation, Sigma, must be used in conjunction with sigma and one or two other parameters which are unique to the process being described in order to compose autocorrelation and power- spectral density functions The conversion from measured to theoretical standard deviation and vice versa in the case of atmospheric turbulence measurement and evaluation, which is restricted to a finite frequency bandwidth, is feasible by means of the dimensionless parameter comprising L and the low frequency cutoff wavenumber L may also be used for the direct calculation of time spectra from space spectra, and it facilitates the accurate treatment of stochastic transients OC A82-41013 # Theoretical and experimental investigation of joint- structural damping interaction for airplane construction. I N Krivosic (Beo- grad, Univerzitet, Belgrade, Yugoslavia) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference. Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 1358-1367 14 refs After considering previously published joint structural damping interaction stud- ies and possible physical models for this phenomenon, experimental results for the case of typical aircraft structures are treated by employing the same geomet- rical model with different types of joints between the skin, stringers and trans- verse elements Separate analyses are given for rivet, bolt and adhesive joints, and the corresponding mutual influence of the amplitude on structural damping is analyzed in light of the experimental results O C A82-41014 # Optimizing aerospace structures for manufacturing cost. B R Noton (Battelle Memorial Institute, Columbus, OH) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings 516 A82-41024 Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1368-1385 The evolution of design/manufacturing interaction reveals the need for design methodologies to reduce aerospace systems cost Cost-driver identification related to performance, design, materials, and manufacturing emphasizes the importance of the preliminary design phase Data are required on designer- influenced cost elements, for example, with composites these are, hybrids, ply count, curing method, and quality requirements A 'Manufacturing Cost/Design Guide' (MC/DG) for composite and metallic airframes, and also electronics, is discussed Using examples of components and fuselage panels, the utilization of designer-oriented formats for relative and quantitative costs of manufacturing processes in trade-studies involving structural performance is shown The MC/DC will also indicate potential cost savings of emerging technologies which accelerate technology transfer (Author) A82-41015 # Composite structures repair. H Wicker (Grumman Aeros- pace Corp. Bethpage, NY) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1386-1392 This paper concerns itself with the repair of composite materials on modern aircraft with particular emphasis on repair techniques and equipment for field use The high strength to weight ratio of composites make them ideal to meet the demand for increasing the performance of military aircraft However, with the increasing use of composite materials, a need has been created for unique repair methods To meet the need to simultaneously apply pressure and a uniform temperature to the patch, a composite repair console and integral vacuum/- heater blanket was developed by Grumman (Author) A82-41016 # Principles of achieving damage tolerance with flexible maintenance programs for new and aging aircraft. J Hall and U G Goranson (Boeing Commercial Airplane Co , Seattle, WA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 1393-1405 Boeing has developed new technology and procedures for determining flexible structural maintenance programs that meet damage tolerance regulations Rat- ing systems, based on past maintenance, are used to develop inspection pro- grams to ensure timely detection of structural damage from environmental deterioration (EDR), accident (ADR), or fatigue (DTR) The inspection program consists of two phases Initially, the program is based on evaluations for detecting corrosion, stress corrosion, and accidental damage using the EDR and ADR systems As the fleet matures, inspection tasks for detecting fatigue damage, based on the DTR evaluations are incorporated into the program (Author) A82-41018 # Intake swirl - A major disturbance parameter in en- gine/intake compatibility. F Aulehla (Messerschmitt-Bolkow-Blohm GmbH, Munich, West Germany) In International Council of the Aeronautical Sciences, Congress. 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1415-1424 10 refs Based on theoretical considerations and primarily on experiment it is shown that all supersonic intakes of present combat aircraft produce essentially two types of swirl components of varying magnitude i e bulk and twin swirl Depend- ing on the sensitivity of the engine towards such disturbances serious engine/in- take compatibility problems may arise, as for example engine surge and fan vibration The remedial measures tp_overcome this problem are described and the solution of fenced intakes selected for Tornado is discussed It is expected that this intake modification may also be of advantage for other high performance combat aircraft having similar intake configurations Finally the relevance of dy- namic total pressure distortion as prime compatibility parameter is questioned and a proposal for an improved intake disturbance simulation in engine bench tests is made (Author) A82-41019 . # An improved propulsion system simulation technique for scaled wind tunnel model testing of advanced fighters. M F Eigenmann, P A Devereaux (McDonnell Aircraft Co , St Louis, MO), and C D Wagenknecht (General Electric Co , Cincinnati, OH) In International Council of the Aeronauti- cal Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Con- ference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1425-1436 10 refs In the interest of accurately evaluating interactions between inlet and nozzle flowfields and between a propulsion system and aerodynamic surfaces, in ad- vanced fighter aircraft having highly integrated and closely coupled propulsion systems, a supersonic propulsion simulator for wind tunnel models has been developed A digital control console system was also developed in order to match model engine operational and control requirements that approximate those of a full scale engine Attention is given to simulator engine components and wind tunnel model installation details, along with the efficient use of the simulator test technique in the various phases of a supersonic aircraft configuration's develop- ment program The thrust/drag accounting system employing the simulator model for studies of basic aerodynamic performance and throttle-dependent effects is flowcharted, and the corrections necessary in each case are assessed OC A82-41020 # Low-speed characteristics of a fighter-type configura- tion at high angles-of-attack and sideslip. K Huenecke (Veremigte Flugtech- nische Werke GmbH, Bremen, West Germany) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Tech- nology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronau- tics, 1982, p 1437-1444 Force measurements and flow observations were conducted on a fighter-type configuration as an aid to understanding the complex flow phenomena occunng at high angles-of-attack, with an, without sideslip The configuration typically was provided with a cranked delta wing of aspect ratio 2 5, leading-edge sweep of 56 deg, wing-mounted vertical tails, and all-moving canard surfaces The results indicate that certain configurational changes, such as vertical tailplane strakes, are sufficient to eliminate an otherwise unstable roll and yaw behavior occunng at around 22 deg angle-of-attack (Author) A82-41021 # Wing design for supersonic cruise/transonic maneuver aircraft. P B Gingrich and E Bonner (Rockwell International Corp , El Segundo, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1445-1453 9 refs An approach to multiple-design-pomt tactical aircraft wing development is dis- cussed Requirements for proposed tactical aircraft include both efficient super- sonic cruise an, acceleration and enhanced transonic maneuvering performance A computational approach was developed to address the conflicting require- ments of these conditions The approach consists of developing two point de- signs a transonic maneuver configuration with weak shocks and nearly attached flow and an optimum supersonic cruise design A compromise is then developed in an iterative cycle which seeks to approach the point design flow quality through the use of variable camber Computational results for representative tactical aircraft are presented to illustrate the process Test experience is discussed to indicate the performance achieved with compromise designs relative to point- design configurations (Author) A82-41022 # " Analysis of jet transport wings with deflected control surfaces by using a combination of 2- and 3-D methods. N J Pfeiffer (Boeing Commercial Airplane Co , Seattle, WA) In International Council of the Aeronauti- cal Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Con- ference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1454-1458 6 refs A computational technique has been developed which analyzes transport wings with deflected spoilers or ailerons It uses 2-D separated flow analysis results in a 'strip theory' fashion to provide inputs for a 3-D lifting surface method Wing body lift and pitching moments are quantitatively predicted and calculated spanloads qualitatively match experimental results The method is accurate and economical enough to be useful in the basic design of control systems (Author) A82-41023 # Optimization of canard configurations - An integrated approach and practical drag estimation method. I M Kroo and T McGeer (Stanford University, Stanford, CA) In International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1459-1469 16 refs A fundamental analysis of subsonic canard configurations illustrates some of the problems associated with such designs and difficulties encountered in their optimization A general solution for minimum induced drag as a function of span ratio, vertical gap, and relative surface lifts is presented Stability and trim require- ments, together with the system geometry then determine the total induced drag and practical conclusions follow when structural weight and stalling speed con- strains are added Required chord and twist distributions are determined, illustrat- ing the problems associated with multiple design points Unlike conventional configurations, the canards' geometric variables associated with optimal solu- tions to each of the above problems vary widely, showing great sensitivity to constraints and off-design operation (Author) A82-41024 * # Wind-tunnel investigation of a full-scale canard-con- figured general aviation aircraft. L P Yip and P F Coy (NASA, Langley Research Center, Hampton, VA) In International Council of the Aeronautical 517 A82-41025 Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Confer- ence, Seattle, WA, August 22-27, 1982, Proceedings Volume 22 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1470-1488 11 refs As part of a broad research program to provide a data base on advanced airplane configurations, a wind-tunnel investigation was conducted in the Langley 30-by 60-Foot Wind Tunnel to determine the aerodynamic cha5 axenstics of an advanced canard-configured general aviation airplane The investigation included measurements of forces and moments of the complete configuratio , isolated canard loads, and pressure distributions on the wing, wmglet, and canard Flow visualization was obtained by using surface tufts to determine regions of flow separation and by using a chemical sublimation technique to determine boundary- layer transition locations Additionally, other tests were conducted to determine simulated ram effects on boundary layer transition Investigation of configuration effects included variations of canard locations, canard airfoil sec on, wmglet size, and use of a leading-edge droop on the out-board section of the wing (Author) A82-41025 # Wind tunnel measurements of longitudinal stability and control characteristics of primary and secondary wing configurations. H L Chevalier (Texas A & M University, College Station, TX) In International Council of the Aeronautical Sciences. Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, WA, August 22-27, 1982, Proceedings Volume 2 (A82-40876 20-01) New York, American Institute of Aeronautics and Astronautics, 1982, p 1489-1494 Low speed wind tunnel measurements of the variations in pitching moment coefficient with angle of attack are described for primary and secondary wing configurations, wing-canard combinations Experimental results are shown for various vertical and horizontal distances between the surfaces, canard incidence angles and canard flap angles These experimental results show that the stability is nonlinear with both angle of attack and incidence angle and as a consequence the pitching moment coefficient at zero lift is an important parameter affecting the stability at trim conditions At high angles of attack, above canard stall, the change in pitching moment coefficients with canard incidence angle and flap angle is reduced and for some configurations the change is reversed Results also show that wind tunnel tests, at the appropriate Reynolds Number, are needed to deter- mine longitudinal stability and control characteristics of wing-canard combina- tions (Author) A82-41055 Monopole antenna patterns on finite size composite ground planes. C A Balanis (West Virginia University, Morgantown, WV) and D DeCarlo (Naval Air Systems Command, Naval Air Test Center, Patuxent River, MD) IEEE Transactions on Antennas and Propagation, vol AP-30, July 1982, p 764-768 9 refs The geometrical theory of diffraction methods is used to develop models and to predict the patterns of communications, navigation, and identification (CNI) blade antennas mounted on finite size composite ground planes The computed patterns are found io agree extremely well with measurements It is shown, both analytically and experimentally, that very minor differences between patterns of antennas mounted on perfectly conducting and composite ground planes appear for conductivities equal to 10,000 sAn The anisotropy effect of the composite material on the antenna patterns is thought to be undetectable, at least within the system measuring accuracy Therefore, perfectly conducting models can be used to analytically investigate the electromagnetic scattering properties of com- posite materials with conductivities equal to or greater than 10,000 s/m C R A82-41075 Heat release rate calonmetry of engineering plastics. A L Bndgman and G L Nelson (General Electric Co , Pittsfield, MA) Journal of Fire and Flammability, vol 13, Apr 1982, p 114-134 27 refs . The Ohio State University Heat Release Rate Calorimeter (OSUHRRC) is examined as a means of defining the fire characteristics of engineering plastics under closely controlled and defined conditions of exposure to incident thermal radiation The principles and operation of the OSUHRRC are described, and examples of tests are presented utilizing engineering thermographics A typical test is described in detail, and the factors affecting the results, including reprodu- cibihty, external heat flux, and sample thickness, are examined The improvement in fire retardancy resulting from the incorporation of flame retardants into test specimens is documented for polycarbonates Comparisons of the results with large-scale foam box tests show the same relative rankings with respect to both temperature and smoke performance . C D A82-41114 # Design of a longitudinal ride-control system by Zakian's method of inequalities. T R Crossley (Salford, University, Salford, England) and A M Dahshan (Military Technical College, Cairo, Egypt) Journal of Aircraft, vol 19, Sept 1982, p 730-738 36 refs In this paper, Zakian's method of inequalities is applied to the design of a ride-control system for a STOL aircraft The purpose of the controller is to reduce the normal acceleration experienced by both passengers and crew The method is based on the synthesis of a controller such that a set of performance specifica- tions and constraints is satisfied Controllers are designed on the basis of the characteristics of both the closed-loop step response and the closed-loop error response It is shown that the design of a single-input, single-output controller by the method of inequalities is straightforward, and can be achieved by using a sequence of formulations until the designer is satisfied that no further improve- ment is necessary (Author) A82-41115 # Fatigue behavior of weldbonded joints. G V Scanch and G R Chanani (Northrop Corp , Aircraft Div , Hawthorne, CA) Journal of Aircraft, vol 19, Sept 1982, p 773-780 7 refs Contract No F33615-76-C-5412 The effects of material and process variables on fatigue behavior were deter- mined for a newly developed, low-cost weldbondmg process for the assembly of durable aircraft structures The weldbondmg process involves spot-welding com- ponents through a previously applied adhesive, and then oven-curing the assem- bly to achieve a bonded structure Both low-load and high-load transfer specimen geometries with each of two alloy combinations (7075-T6/7075-T6 and 2024-T3 alclad/7075-T6) were evaluated Fatigue behavior of weldbonded specimens with different nugget sizes and different manufacturing defects was compared with that of riveted and adhesive-bonded specimens In low-load transfer fatigue, weldbondmg was better than nvetmg, but not as good as adhesive bonding, while in high-load transfer fatigue, weldbondmg was equal to or better than riveting and adhesive bonding (Author) A82-41116 # Minimum induced drag of canard configurations. I M Kroo Journal of Aircraft, vol 19, Sept 1982, p 792-794 10 refs Drag estimations are made for an elliptically loaded wing on an aircraft equipped with canards An analysis of Prandtl's biplane equation, along with Monk's stagger theorem (1921), shows that a minimum induced drag occurs when the total loading is elliptical over the wing span, with lift transferred toward the outboard section of the wings The section lift of the wing is represented as a Fourier series and a resulting lift distribution defines a minimum induced drag Prandtl's interference factor is calculated and a nonelliptic interference factor is defined and is used to demonstrate that a substantial reduction in induced drag is possible in comparison with the elliptically loaded case M S K A82-41117 # Estimation of the number of in-flight aircraft on instru- ment flight rules. N Myerhoff and J Garlitz (U S Department of Transportation, Office of Air and Marine Systems, Cambridge, MA) Journal of Aircraft, vol 19, Sept 1982, p 794-796 FAA-supported research Mathematical models for estimating the instantaneous aircount (IAC) of aircraft on instrument flight rules flying over the U S at any moment are described The data is gathered from the Official Airline Guide for scheduled great circle paths and proiections are made for the location of aircraft at any time of day The estimates are made independent of radar target reports and cover the regions monitored by each of the 20 air route traffic control centers on the continent Noting that arrivals and departures are approximately equal from individual cen- ters' jurisdiction at any moment, probabilities are generated for the presence of an aircraft in any given time interval, and a standard profile is employed in regions where a specific flight profile is unknown Accuracy has been shown to be within 10% during peak hours M S K A82-41140 Recommended practice for a demonstration of Nonde- structive Evaluation /NDE/ reliability on aircraft production parts - Intro- duction to the guidelines. W D Rummel (Martin Marietta Aerospace, Denver, CO) Materials Evaluation, vol 40, Aug 1982, p 922-932 Guidelines for a demonstration of Nondestructive Evaluation (NDE) reliability on aircraft production parts have been compiled in order to promulgate recom- mended practices for the development of repeatable data in fracture mechanics applications Such practices are designed to demonstrate the capabilities of various NDE methods for the detection of flaws in specific materials or parts under routine production inspection conditions The intent of the guidelines is to define the limiting flaw size which can be detected within a given probability of detection and with a given percent of confidence in that probability The outline presented encompasses operational requirements, the acquisition and reduction of data, and requalification procedures O C A82-41141 Evaluation of heat damage to aluminum aircraft struc- tures. D J Hagemaier (Douglas Aircraft Co , Long Beach, CA) Materials Evalu- ation, vol 40, Aug 1982, p 962-969 15 refs Examinations of, heated surface discoloration or distortion, eddy current con- ductivity comparison tests and hardness tests are used to evaluate the degree of heat damage incurred by aluminum alloy aircraft structures Data from articles and reports on the exposure of 7075-T6 and 2024-T3/T4 aluminum alloy sheet materials to elevated temperatures for extended periods of time are considered, and portable hardness and eddy current test equipment for damage assessment are described with attention to significant variables affecting conductivity read- ings The data presented suffice for the substantiation of a direct relationship between conductivity, hardness and strength which will allow the evaluation of heat or fire damage in heat-treatable aluminum alloys O C 518 A82-41575 A82-41447 # Visual scene simulation concerning the landing of sporting aircraft in connection with investigations regarding the control and learning behavior of the pilot (Sichtsimulation der Landung von Sport- flugzeugen im Hinblick auf Untersuchungen zum Regler- und Lernverhalten des Piloten). W Heumann Darmstadt, Techmsche Hochschule, Fachbereich Regelungs- und Datentechnik. Dr-lng Dissertation, 1980 268 p 89 rets In German Research supported by the Deutsche Forschungsgememschaft The present investigation is concerned with the behavior of man as controller in a technical system The obiect of the studies, which were conducted with the aid of a simulator providing a visual scene presentation, is the control of the longitudinal motion of a sporting aircraft during the last phases of a landing under visual flight conditions Attention is given to the behavior of flying students, taking into account differences in the behavior of students and experienced pilots Changes in the behavior of the student in connection with advances related to the learning process are examined The landing simulation system employed pro- vides a presentation of the visual environment of the pilot during the landing procedure, and, in addition, also a lateral view of the landing aircraft This ap- proach has certain advantages for the student from a didactic point of view The analysis of the flight path with the aid of the simulator makes it possible to develop a basic model which is typical for a landing performed by an experienced pilot GR A82-41453 # Investigations concerned with shifting pilot activities to a higher hierarchical stage of flight control (Untersuchungen zur Ver- lagerung der Pilotentatigkeit auf eine hohere hierarchlsche Stufe der Flug- fuhrung). P Sundermeyer Braunschweig, Techmsche Umversitat, Fakultat fur Maschmenbau und Elektrotechmk, Dr-Ing Dissertation, 1980 120p 26 refs In German Advantages and drawbacks of the automation of flight control systems are discussed, taking into account various hierarchical planes The result of this system analysis is the concept of an aircraft guidance computer for the onboard four-dimensional flight path calculation and generation The developed computer system becomes a component of an integrated flight guidance system The computer makes it possible to conduct studies by which the activities to be performed by the pilot are raised to a higher level, involving the solution of coordination problems The computer calculates possible alternatives regarding the flight path for the aircraft The pilot makes the final decision on the basis of the information provided by the computer In addition to performing a calculation of the flight path, the computer provides a representation of the flight path on a map display, time control information, and flight guidance activities (four-dimen- sional) with respect to different stages of automatization G R A82-41575 t High-sensitivity holographic plates PL-3M (Vysoko- chuvstitel'nye golograficheskie plastinki PL-3M). L la Kaplun, E F Klimzo, and E N Sergeeva (Vsesoiuznyi Gosudarstvennyi Nauchno-lssledovatel'sku i Proektnyi Institut Khimiko-Fotograficheskoi Promyshlennosti, Moscow, USSR) Zhurnal Nauchnoi i Pnkladnoi Fotografu i Kinematografu, vol 27, July-Aug 1982, p 293-295 8 refs In Russian High-sensitivity holographic plates have been obtained by using spectrally sensitized ultrafme-gramed emulsion with pAg = 68 The plates, designated PL-3M, have a light sensitivity of 100 erg/sq cm and a diffraction efficiency of 4 3% The high-sensitivity holographic plates are currently used in research con- cerned with holographic mterferometry of aircraft structures, development of holographic memory devices, stress and strain analysis of structures and materi- als, lens testing, and optical recording of analog information V L 519 Page Intentionally Left Blank N82-28262 STAR ENTRIES 22-27 Aug 1982. sponsored by the American Inst of Aeronautics and Astronautics Previously announced in IAA as A82-16902 (NASA-TM-82885 E-1263. NAS 11582885) Avail NTIS HC A02/MF A01 CSCL 01A For abstract see A82-16902 N82-28243*# Lockheed-California Co , Burbank ELECTRONIC/ELECTRIC TECHNOLOGY BENEFITS STUDY Report. Aug. 1980 - Jan. 1982 W W Howison and M J Cronin May 1982 226 p (Contract NAS1-16199) (NASA-CR-165890. NAS 126165890. LR-30079) Avail NTIS HC A11/MF A01 CSCL01B The benefits and payoffs of advanced electronic/electric technologies were investigated for three types of aircraft The technologies, evaluated in each of the three airplanes, included advanced flight controls, advanced secondary power advanced aviontc complements, new cockpit displays, and advanced air traffic control techniques For the advanced flight controls, the near term considered relaxed static stability (RSS) with mechanical backup The far term considered an advanced fly by wire system for a longitudinally unstable airplane In the case of the secondary power systems, trades were made in two steps in the near term, engine bleed was eliminated, in the far term bleed air. air plus hydraulics were eliminated Using three commercial aircraft. In the 150, 350, and 700 passenger range, the technology value and pay-offs were quantified, with emphasis on the fiscal benefits Weight reductions deriving from fuel saving and other system improvements were identified and the weight savings were cycled for their impact on TOGW (takeoff gross weight) and upon the performance of the airframes/engmes Maintenance, reliability and logistic support were the other criteria Author N82-28244# Federal Aviation Administration. Washington, D C Office of Management Systems GENERAL AVIATION ACTIVITY AND AVIONICS SURVEY Annual Report Judith C Schwenk Dec 1981 205 p refs (AD-A112924, FAA-MS-81-5) Avail NTIS HC A10/MF A01 CSCL 01/2 This report presents the results and a description of the 1980 General Aviation Activity and Avionics Survey The survey was conducted during 1981 by the FAA to obtain information on the activity and avionics of the United States registered general aviation aircraft fleet, the dominant component of civil aviation in the U S The survey was based on statistically selected sample of about 140 percent of the general aviation fleet and obtained a response rate of 65 percent Survey results are based upon responses but are expanded upward to represent the total population Survey results revealed that during 1980 an estimated 41 0 million hours of flying time were logged by the 211.045 active general aviation aircraft in the U S fleet, yielding a mean annual flight time per aircraft of 1905 hours The active aircraft represented about 83 percent of the registered general aviation fleet The report contains breakdowns of these and other statistics by manufacturer/model group, aircraft type, state and region of based aircraft, and primary use Also included are fuel consumption, lifetime airframe hours, avionics, and engine hours estimates Author (GRA) N82-28245# Air Force Systems Command. Wright-Patterson AFB, Ohio Foreign Technology Div INTERNATIONAL AVIATION (SELECTED ARTICLES) 12 Apr 1982 23 p Transl into ENGLISH from GuO|i Hangkong (Communist China), no 224, Oct 1981 p 2-9. 49 (AD-A114422. FTD-ID(RS)T-0027-82) Avail NTIS HC A02/MF A01 CSCL 21/5 Chinese made goods were exhibited, including aeronautical forgings, castings, forging dies, casting molds, powder metallurgi- cal products, and titanium alloys and products These goods symbolize China's production capability and technical level of aeronautical forgings and castings, with excellent qualities of these products S L N82-28249*# National Aeronautics and Space Administration Lewis Research Center, Cleveland, Ohio A SUMMARY OF V/STOL INLET ANALYSIS METHODS Danny P Hwang and John M Abbott 1982 17 p refs To be presented at the 13th Congr of the Intern Council of the Aeronautical Sci and Aircraft Systems and Technol Conf, Seattle. N82-28252*# National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif AERODYNAMIC INTERACTIONS BETWEEN A 1/6 SCALE HELICOPTER ROTOR AND A BODY OF REVOLUTION Mark D Betzma and Patrick Shinoda Jun 1982 15 p refs Prepared in cooperation with Army Research and Technology Labs . Moffett Field. Calif (NASA-TM-84247 A-8940 NAS 11584247) Avail NTIS HC A02/MF A01 CSCL 01A A wind-tunnel investigation was conducted in which in- dependent, steady state aerodynamic forces and moments were measured on a 2 24-m-diam. two bladed helicopter rotor and a body of revolution The objective was to determine the interaction of the body on the rotor performance and the effect of the rotor on the body aerodynamics for variations in velocity thrust, tip-path-plane angle of attack, body angle of attack, rotor/body position, and body nose geometry Results show that a body of revolution near the rotor can produce significant favorable or unfavorable effects on rotor performance, depending on the operating condition Body longitudinal aerodynamic characteristics are Significantly modified by the presence of an operating rotor and hub Author N82-28260# Systems Research Labs, Inc Dayton, Ohio WIND-TUNNEL EVALUATION OF AN AEROELASTICALLY CONFORMABLE ROTOR Final Report Lawrence R Sutton Richard P White, Jr. and Robert L Marker Mar 1982 87 p refs (DA Pro) 1L2-62209-AH-76) (AD-A1 14384. U SAAVRADCOM-TR-81-0-43) Avail NTIS HC A05/MF A01 CSCL 01/3 This report summarizes the theoretical and experimental investigations that were conducted to evaluate the potential of aeroelastic and mass-elastic couplings in an aerolastic conformable rotor (ACR) that will improve the performance and vibratory characteristics of helicopter rotor systems without creating instabilities ACR parameters were identified and a baseline rotor system was selected An ACR blade concept was investigated by altering the characteristics of the baseline and using auto- mated analysis techniques GRA N82-28261# Army Aviation Research and Development Command. St Louis Mo Applied Technology Lab NATIONAL TRANSONIC FACILITY (NTF) PROTOTYPE FAN BLADE FATIGUE TEST Progress Report. Jan. - Mar 1981 E H Dean, A J Gusiafson and D M Saylor Mar 1982 18 p (DA Pro) 1L1-62209-AH-76) (AD-A1 14405 USAAVRADCOM-TR-82-D-5 ) Avail NTIS HC A02/MF A01 CSCL 14/2 The Applied Technology Laboratory conducted fatigue tests on a composite fan blade designed for use in the new NTF wind tunnel being constructed at NASA-Langley The tests were performed by the Structures Technical Area using the root end fatigue machine (REFM) which was modified for ground air ground testing Simulated centrifugal and aerodynamic Ibendmgl load tests were performed The fan blade successfully withstood 6000 cycles at 360 rpm and 600 rpm load conditions foi the cyclic rate tests These tests simulated the starting and stopping cycles of the fan Static load tests to 57 000 pounds design load were also successfully performed on the blade specimen Author (GRA) N82-28262# National Aerospace Lab Amsterdam (Netherlands) Fluid Dynamics Div EVALUATION OF AN EXPERIMENTAL TECHNIQUE TO INVESTIGATE THE EFFECTS OF THE ENGINE POSITION ON ENGJNE/PVLON, WING INTERFERENCE J A J vanEngelen B Munniksma. and A Elsenaar 28 Apr 1981 16 p refs Presented at AGARD Symp on Aerodyn of Power Plant Installation Toulouse 11-14 May 1981 (NLR-MP-81020-U) Avail NTIS HC A02 MF A01 Free flow and blown nacelle wind tunnel testing of engine airframe integration are compared and the magnitude of the parasitic interference of an additional strut and engine inlet fairing 521 N82-28263 is examined A semispan model, typical of a transport aircraft with a supercritical wing was tested A 3/4 fan cowl high bypass engine was located at six positions underneath the wing Measurements included pressure and balance force It is shown that while accurate simulation of engine nozzle geometry is of prime importance, tests on free flow nacelles are useful for selecting engine position Interference forces derived from pressure integration are only useful for determining trends in interference effects for flexible initial tests Author IESA) N82-28263# National Aerospace Lab . Amsterdam (Netherlands) Informatics Div A FINITE DIFFERENCE METHOD FOR THE CALCULATION OF TRANSONIC FLOW ABOUT A WING. BASED ON SMALL PERTURBATION THEORY J vanderVooren. G H Huizing and A vanEssen 5 Mar 1981 103 p refs (Contract NIVR-1739) (NLR-TR-81031-U) Avail NTIS HC A06/MF A01 A calculation method for the transonic flow about a semiwing based on transonic small perturbation theory, is presented The influence of a body can be simulated by prescribing appropriate transverse velocities in a vertical plane through the wing root The wing should be thin and have little dihedral, camber and twist and a not too blunt leading edge The body should be slender The angle of incidence must be small However, highly swept wings are allowed A fully finite difference scheme is implemented for a correct shock capture Line relaxation is used to solve the corresponding nonlinear equations It is indicated that too much artificial viscosity leads to an unrepresentative calculation, and too little can lead to instabilities Author (ESA) N82-28264# General Accounting Office. Washington. D C Accounting and Financial Management Div COMPUTER OUTAGES AT AIR TERMINAL FACILITIES AND THEIR CORRELATION TO NEAR MISS MID-AIR COLLI- SIONS (AFMD-82-43) 16 Feb 1982 17 p refs (B-206064) HC A02/MF A01 The frequency of computer failures at terminal facilities and the extent of correlation between these failures and near mid-at collisions were investigated in a survey of nine terminal facilities No direct correlation between the computer outages and reported mid-air collisions or the safety related incidents was found RJ F N82-28265# Aeronautical Research Labs . Melbourne (Australia) A STUDY OF WIND SHEAR EFFECTS ON AIRCRAFT OPERATIONS AND SAFETY IN AUSTRALIA K W Anderson and B A J Clark Mar 1981 84 p refs (ARL-Sys-Rept-24 AR-002-271) Avail NTIS HC A05/MF A01 The ergonomics aspects of aircraft operation in conditions of local variations of wind were studied Questionnaires were analyzed for subject understanding, detection of wind difficulties, frequency of wind shear and downdraft situations, pilot techniques, and forewarning methods Pilots often found terrain-induced downdrafts and thunderstorm wind shears troublesome Opera- tions in irregular terrain away from major aerodromes were frequently cited for wind shear hazards Pilot judgements on the most susceptible aircraft types were not readily explicable in terms of size, landing speed or wing loading Pilots and ATCs indicated that currently used cues in wind shear conditions include visual estimates of glideslope departures precision approach radar observations and aircraft-based measurements of wind or ground speed Ground-based remote sensing equipment for detecting stable wind shear is considered A synopsis of wind-involved airliner crashes and a summary of meteorological conditions for the occurrence of local wind variations are included Author N82-28266'# Villanova Univ Pa GUST RESPONSE OF COMMERCIAL JET AIRCRAFT INCLUDING EFFECTS OF AUTOPILOT OPERATION Final Report Joseph H Goldberg Jun 1982 125 p refs (Contract NAS1-16095) (NASA-CR-165919) Avail NTIS HC A06/MF A01 CSCL 01C A simplified theory of aircraft vertical acceleration gust response based on a model including pitch, vertical displacement and control motions due to autopilot operation is presented High-order autopilot transfer functions are utilized for improved accuracy in the determination of the overall response characteris- tics Four representative commercial jet aircraft were studied over a wide range of operating conditions and comparisons of individual responses are given It is shown that autopilot operation relative to the controls fixed case causes response attenuation of from 10 percent to approximately 25 percent depending on flight condition and increases in crossing number up to 30 percent, with variations between aircraft of from 5 percent to 10 percent, in general, reflecting the differences in autopilot design A detailed computer program description and listing of the calculation procedure suitable for the general application of the theory to any airplane autopilot combination is also included Author N82-28267# Aerospace Medical Research Labs. Wright- Patterson AFB. Ohio Biomechanical Protection Branch COMPARATIVE VERTICAL IMPACT TESTING OF THE F/FB-111 CREW RESTRAINT SYSTEM AND A PROPOSED MODIFICATION Bernard F Hearon. James W Brmkley James H Raddm Jr. Lawrence A McGowan and Joseph M Powers Mar 1982 312 p refs (AF Proj 7231) (AD-A113957 AFAMRL-TR-82-13) Avail NTIS HC A13/MF A01 CSCL 01/3 An impact test program was conducted to evaluate the operational F/FB-111 crew seat and restraint system and a proposed modification A primary objective of the program was to compare human response to vertical impacts in the two restraint harnessess A total of 67 human impact tests were performed on the Vertical Deceleration Tower up to 10 G peak 26 ft/sec Subjects were exposed to comparable impacts at different seat elevations in both harnesses to allow parametric analysis of the test results Measured data included seat acceleration and velocity head and chest translational acceleration components, tnaxial forces acting on the seat and footrest, forces acting at the restraint harness, attachment and deplacements of various body segments The resultant head and chest accelerations were significantly greater in the modified harness than in the operational harness, regardless of seat elevation On the basis of this comparison, the proposed modification to the F/FB-111 crew seat and restraint is not recommended for implementation Future restraint harness modification proposals should be based on careful evaluation of all unconventional design features of the operational harness and should address all mechanisms by which adverse loads may be imposed on the seat occupant In addition future redesign efforts of the F/FB-111 escape system should provide improved landing impact attenuation GRA N82-28268# Air Force Engineering and Services Center Tyndall AFB. Fla Engineering and Services Lab SMOKE ABATEMENT SYSTEM FOR CRASH RESCUE/FIRE TRAINING FACILITIES Final Report. Sep. 1979 - Sep. 1981 Anthony J Kwan and John A Hamre Sep 1981 33 p (AF Proj 2505) (AD-A114380 AFESC/ESL-TR-81-43) Avail NTIS HC A03/MF A01 CSCL 13/2 This report provides the design for a smoke-abated aircraft crash/rescue trainer The design is for a 75-ft diameter fire area suitable for operation in freezing and nonfreezing climates With this system liquid petroleum fuels can be burned with little or no smoke by injecting a fine water spray near the surface of the burning fuel This method of smoke abatement is being applied at military fire fighting training facilities The report includes dll equipment necessary for the smoke abatement function and provides detailed step-by-step operating procedures Author (GRA) N82-28269*# Analytical Mechanics Associates. Inc . Hampton. Va TERMINAL AREA AUTOMATIC NAVIGATION. GUIDANCE, AND CONTROL RESEARCH USING THE MICROWAVE LANDING SYSTEM (MLS). PART 4 TRANSITION PATH RECONSTRUCTION ALONG A STRAIGHT LINE PATH CONTAINING A GLIDESLOPE CHANGE WAYPOINT Final Report Samuel Pines Washington NASA Jun 1982 40 p refs (Contract NAS1-15116) 522 N82-28282 Army Aviation Engineering Flight Activity. Edwards AFB. Calif Directorate for Development and Qualification HISS CALIBRATION, ICE PHOBICS AND FAA R/D EVALUATIONS Final Report. Jan. - Mar. 1981 John C Henderson. Ralph Woratschek. and Loran A Haworth Aug 1981 62 p refs (AD-A114435. USAAEFA-80-13) Avail NTIS HC A04/MF A01 CSCL 01/3 Artificial and natural icing tests of a JUH-1H helicopter were flown in the vicinity of St Paul. Minnesota, during the three month period of January through March 1981 Productive flight time totaled 154 hours in the artificial icing environment behind the Helicopter Icing Spray System (HISS) and 3 2 hours in natural icing Test conditions ranged from -5 C to -20 C and 0 25 to 1 0 gram per cubic meter liquid water content (LWC) for the artificial testing and -6 C to -9 C and 01 to 0 5 gram per cubic meter LWC for the natural testing Tests in the artificial icing environment behind the HISS were flown to define the nature of the HISS cloud in terms of LWC. cloud particle size and distribution, and to quantitatively determine the effects of an ice phobic coating on the capability of the UH-1H to fly in 524 N82-28296 icing conditions The ice phobic coating did not significantly affect the capability of the UH-1H to fly in icing conditions GRA N82-28290# Army Aviation Research and Development Command. St Louis. Mo HISTORICAL RESEARCH AND DEVELOPMENT INFLATION INDICES FOR ARMY FIXED AND ROTOR WINGED AIRCRAFT Annual Report Charles W Lines. Jr and William J Waymire Jan 1982 37 p refs (AD-A114368. USAAVRADCOM-TR-82-F-3) Avail NTIS HC A03/MF A01 CSCL 05/1 This Technical Memorandum is a continuation of previous efforts to develop the necessary rationale and methodology needed in order to construct historical inflation indices, in the Research and Development (R&D) area, relative to Army aircraft The R&D historical indices, and the sub-indices from which they are derived, are presented in the appendices to this report for the period FY68 through FY81 These indices are appropriate for updating statistical reports that formerly utilized the OSD forecasting indices, for initial use in bringing a cost in prior years to a present-year dollar value, and for evaluating inflation actually experienced A computer program is utilized to make the necessary mathematical calculations Data sources for this report were the Office of Personnel Management (0PM) and the Bureau of Labor Statistics (BLS) 0PM supplied data on government salaries BLS furnished data on industry salaries and thirteen different materials The computer program prints the R&D historical inflation indices and subindices by fiscal year as shown in Appendices C through G of this report GRA N82-28291# INCOSYM. Inc. Westlake Village. Calif LOW COST DEVELOPMENT OF INS SENSORS FOR EXPENDABLE RPV CONTROL AND NAVIGATION Final Report. Apr 1979 - May 1981 D G Kim and James G Russell Wright-Patterson AFB. Ohio AFWAL Aug 1981 71 p (Contract F33615-79-C-3616) (AD-A112691, 'AFWAL-TR-81-3086) Avail NTIS HC A04/MF A01 CSCL 01/3 A two year development effort has resulted in the design, fabrication and test of a feasibility model 3-axis vibrating beam accelerometer and a brassboard cycloidal magnetic vector sensor The cycloidal magnetic vector sensor is based on a rotating coil technique which eliminates slip rings It performed as expected, and demonstrated an accuracy of approximately 0 25 degrees The 3-axis vibrating beam accelerometer is based on the principle that a vibrating beam will change its frequency as a function of the applied tension Using six beams, two per sensing axis, connected to a common mass, a 3-axis accelerometer can be designed Such a design measures acceleration, by a change in beam vibration frequency, as a function of applied acceleration to the mass The accelerometer, at first, demonstrated an msensitivity due to frequency lock between the beams This effect was eliminated, but the necessary change in design caused an unstable bias and non-linearity of the scale factor A solution to these problems was also conceived, and hardware changes made However, to fully demonstrate the concept requires a computer and software, which is outside the scope of this program Author (GRA) N82-28292# Environmental Research Inst of Michigan, Ann Arbor Radar and Optics Div DESIGN STUDY FOR A LOW-DISTORTION HOLOGRAPHIC HUD Final Technical Report. Jul. 1980 - Aug. 1981 W S Colburn and R C Fairchild Wright-Patterson AFB, Ohio AFWAL Jan 1982 104 p refs (Contract F33615-80-C-1077) (AD-A113982 AFWA L -TR-81 -1 263. ERIM-1 50800-29-F) Avail NTIS HC A06/MF A01 CSCL 14/5 A low distortion holographic HUD optical system was examined Distortion correction was based on the use of a holographic combiner made with analytically defined construction wavefronts, wavefronts for which the phase at the hologram is described by mathematical expressions Such wavefronts are designed subsequent to the hologram design, and offer great design flexibility as their realization is based in part on the use of computer generated holograms A method for designing the construction wavefronts of a holographic optical element based on minimizing the mean squared wavefront error while satisfying the Bragg condition is described A holographic HUD optical system was designed for the F 16 cockpit in which distortion was corrected optically through simultaneous optimization of combiner and relay lens parameters Both construction wave- fronts of the combiner were described in terms of Legendre polynomial series The implementation of construction beams required to form the combiner construction wavefronts is discussed ' Author (GRA) N82-28293jjf Federal Aviation Administration Atlantic City N J A COMPENDIUM OF LIGHTNING EFFECTS ON FUTURE AIRCRAFT ELECTRONIC SYSTEMS Final Report Nickolus O Rasch Feb 1982 257 p refs Proc of Conf held at Hampton, Va, 4-6 Nov 1981 (AD-A114117. DOT-FAA-CT-82-30) Avail NTIS HC A12/MF A01 CSCL 01/3 This publication is a composite of presentations given at the NASA-Langley Research Center/FAA Technical Center 'Lightning Effects on Future Aircraft Systems Workshop held on November 4-6. 1981, at the NASA-Langley Research Center Facility The presentations encompassed the full spectrum of lightning research from lightning phenomenology lightning modeling, electromagnetic issues associated with composite materials, to the lightning/aircraft electromagnetic interaction analysis Also included are a total of five presentations assessing the Digital System upset phenomena Author (GRA) N82-28294| Grumman Aerospace Corp , Bethpage. N Y HYDRAULIC UNIVERSAL DISPLAY PROCESSOR SYSTEM (HUDPS) Final Report. 1 Apr. - 1 Sep. 1981 John J Duzich and Herman L Dreksler Warmmster Pa Naval Air Development Center 21 Nov 1981 66 p refs (Contract N62269-81-C-0243) (AD-A114428. NADC-82053-60) Avail NTIS HC A04/MF A01 CSCL 01/3 This six month study effort explored methods of display fault indication to ground support personnel and optimize microproces- sion circuitry for universal aircraft application Task I was established the maximum number of sensors required for a complex, comprehensive diagnostic system for the F14A as 150 Inputs could be either analog or digital For comparison purposes, an A6E system was considered Fault display methods were investigated with emphasis on smart alphanumeric devices in Task II Volatile and non-volatile memory components were utilized along with the Intel 8748 microprocessor and associated EPROMS The use of National Semiconductor ADC0816 data acquisition chips consisting of a 16 input multiplexer, an 8 bit A/D converter and an 8 bit tn-state buffered output facilitates the many inputs Power consumption for a complete system was estimated as 5 watts while airborne On the ground. 15 watts at 5 volts is required for display requirements Display envelope would measure 8x7x6 and would contain approximately 6 circuit boards In Task III a universal display processor system was formulated A Block Diagram and several flow diagrams were generated Multiplexer schematics were established for analog and discrete inputs An electrical component parts list was generated for a typical system Author (GRA) N82-28295*# National Aeronautics and Space Administration Ames Research Center, Moffett Field, Calif STATIC NOISE TESTS ON MODIFIED AUGMENTOR WING JET STOL RESEARCH AIRCRAFT G R Cook and B F Lilley (deHavilland Aircraft of Canada. Ltd. Downsview, Ontario) Feb 1981 58 p refs (NASA-TM-81231. NAS 11581231) Avail NTIS HC A04/MF AOJ CSCL 2IE Noise measurements were made to determine if recent modifications made to the bifurcated jetpipe to increase engine thrust had at the same time reduced the noise level The noise field was measured by a 6-microphone array positioned on a 30 5m (100 ft) sideline between 90 and 150 degrees from the left engine inlet Noise levels were recorded at three flap angles over a range of engine thrust settings from flight idle to emergency power and plotted in one-third octave band spectra Little attenuation was observed at maximum power, but significant attenuation was achieved at approach and cruise power levels TM N82-28296*# Pratt and Whitney Aircraft Group, East Hartford Conn Commercial Products Div B747/JT9D FLIGHT LOADS AND THEIR EFFECT ON 525 N82-28297 ENGINE RUNNING CLEARANCES AND PERFORMANCE DETERIORATION; BCAC NAIL/P AND WA JT9D ENGINE DIAGNOSTICS PROGRAMS W J Olsson and R L Martin 19 Feb 1982 74 p refs Prepared in cooperation with Boeing Commercial Airplane Co , Seattle (Contracts NAS3-20632 NAS1-15325) (NASA-CR-165573. NAS 1 26 165573 PWA-5512-88) Avail NTIS HC A04/MF A01 CSCL 21E Flight loads on the 747 propulsion system and resulting JT9D blade to outer airseal running clearances during representa- tive acceptance flight and revenue flight sequences were measured The resulting rub induced clearance changes, and engine performance changes were then analyzed to validate and refine the JT9D-7A short term performance deterioration model Author N82-28297*# General Electric Co . Cincinnati. Ohio Aircraft Engine Group CF6 JET ENGINE PERFORMANCE IMPROVEMENT: HIGH PRESSURE TURBINE ACTIVE CLEARANCE CONTROL S E Rich and W A Faschmg Jun 1982 136 p refs (Contract NAS3-20629) (NASA-CR-165556. NAS 1 26 165556. R82AEB198) Avail NTIS HC A07/MF A01 CSCL21E An active clearance control system was developed which reduces fuel consumption and performance degradation This system utilizes compressor discharge air during takeoff and fan discharge air during cruise to impinge on the shroud structure to improve the thermal response The system was evaluated in component and engine tests The test results demonstrated a performance improvement of 0 7 percent in cruise SFC S L N82-28298*# Bolt. Beranek and Newman. Inc. Cambridge. Mass ANALYTICAL AND SIMULATOR STUDY OF ADVANCED TRANSPORT Final Report William H Levison and William W Rickard (Douglas Aircraft Co, Long Beach Calif) Washington NASA Jun 1982 86 p refs (Contract NAS1-16410) (NASA-CR-3572. NAS 1 26 3572. Rept-4778) Avail NTIS HC A05/MF A01 CSCL 01C An analytic methodology, based on the optimal-control pilot model was demonstrated for assessing longitudinal-axis handling qualities of transport aircraft in final approach Calibration of the methodology is largely in terms of closed-loop performance requirements, rather than specific vehicle response characteristics, and is based on a combination of published criteria, pilot preferences, physical limitations, and engineering [udgment Six longitudinal-axis approach configurations were studied covering a range of handling qualities problems, including the presence of flexible aircraft modes The analytical procedure was used to obtain predictions of Cooper-Harper ratings, a solar quadratic performance index, and rms excursions of important system variables T M N82-28299*# National Aeronautics and Space Administration Langley Research Center, Hampton, Va METHODOLOGY FOR DETERMINING ELEVON DEFLEC- TIONS TO TRIM AND MANEUVER THE DAST VEHICLE WITH NEGATIVE STATIC MARGIN Boyd Perry, III May 1982 50 p refs (NASA-TM-84499 NAS 11584499) Avail NTIS HC A03/MF A01 CSCL 01 C The relationships between elevon deflection and static margin using elements from static and dynamic stability and control and from classical control theory are emphasized Expressions are derived and presented for calculating elevon deflections required to trim the vehicle in Ig straight-and-level flight and to perform specified longitudinal and lateral maneuvers Applications of this methodology are made at several flight conditions for the ARW-2 wing On the basis of these applications it appears possible to trim and maneuver the vehicle with the existing elevens at -15% static margin Author N82-28301# Virginia Univ , Charlottesville Dept of Mechanical and Aerospace Engineering LIMITING PERFORMANCE OF NONLINEAR SYSTEMS WITH APPLICATIONS TO HELICOPTER VIBRATION CONTROL PROBLEMS Final Report Walter D' Pilkey 1982 26 p refs (Grant DAAG29-79-G-0015) (AD-A 113239, UVA/525098-MAE-82/10, ARO-16091 5-E) Avail NTIS HC A03/MF A01 CSCL 20/11 This report summarizes the accomplishments of a study exploring new methods for the vibration control of helicopters Reanalysis methodology permits a variety of vibration control problems to be solved efficiently Both analytical and experimental studies have been conducted Author (GRA) N82-28302# Air Force Human Resources Lab. Brooks AFB. Tex MANUAL REVERSION FLIGHT CONTROL SYSTEM FOR A-10 AIRCRAFT PILOT PERFORMANCE AND SIMULATOR CUE EFFECTS Final Report Thomas H Gray Mar 1982 31 p refs (AF Pro) 1123) (AD-A113463. AFHRL-TR-81-53) Avail NTIS HC A03/MF A01 CSCL 14/2 The A-10 aircraft incorporates an emergency backup control mode, the Manual Reversion Flight Control System (MRFCS) Maintaining effective control in this mode is a demanding pilot task, but it is not practiced in the flying training syllabus Because current plans call for training this skill using simulation, information was needed on simulator cue requirements Ac- cordingly, the research objective was to determine the effective- ness of selected simulator visual and force cues used by experienced A-10 pilots to maintain aircraft control and to land when in the MRFCS mode The study found that (1) a large field of view enhanced the pilot's control of the aircraft. (2) platform motion had no influence upon aircraft control. (3) aircraft control was more difficult in the MRFCS mode than in the simple single engine failure state, (4) point of failure was a significant variable reliably affecting pilot control of the aircraft, and (5) pilot performance improved as a function of practice (trials) Author (GRA) N82-28303# National Aerospace Lab . Amsterdam (Netherlands) Structures and Materials Div THE DETERMINATION OF GUST LOADS ON NONLINEAR AIRCRAFT USING A POWER SPECTRAL DENSITY APPROACH R Noback and C Laauboder 17 Dec 1980 80 p refs (Contract NIVR-RB-1854) (NLR-TR-80123-U) Avail NTIS HC A05/MF A01 Since the power spectral density method cannot determine the exceedance of the output over the input in the nonlinear equations which describe an aircraft subjected to atmospheric turbulence, methods which approximate the exceedance curve were developed One method is analogous to the classical expression for the equivalent gain Another is analogous to the equivalent gain based on minimum error in energy In both, the maximum value (mu zy) of the cross correlation function between output and input to the nonlmeanty is used A reasonable estimate of the exceedance curve, for systems for which mu zy is not known, can be obtained if the correlation between the input to the nonlmeanty (z) and the system output (y) is high The ratio of the standard deviations of z and y can then be used Design loads based on mission analysis can be established once the load exceedance curve due to constant standard deviation of the input is known A definition for the design load of nonlinear aircraft using the design envelope method is proposed Author (ESA) N82-28306# Seville Research Corp , Pensacola, Fla OPERATIONAL TEST AND EVALUATION HANDBOOK FOR AIRCREW TRAINING DEVICES. VOLUME 3: OPER- ATIONAL SUITABILITY EVALUATION Final Report William V Hagm, Stephen R Osborne. Roik L Hockenberger, James P Smith, and Thomas H Gray (Operations Training Div . Williams AFB. Ariz) AFHRL Brooks AFB. Tex Feb 1982 128 p refs (Contract F33615-78-C-0063. AF Proj 1123! (AD-A112569. AFHRL-TR-81-44-Vol-3) Avail NTIS HC A07/MF A01 CSCL 05/9 The Handbook is comprised of three volumes and is intended to provide guidelines and procedures appropriate for Air Force Operational Test and Evaluation (OT&E) personnel to use in planning, conducting and reporting the results of simulator assessment efforts Although of value to all test personnel, it is 526 N82-28462 primarily for the typical novice test manager/director - a person who has subject matter expertise (e g . a qualified pilot or operator), but who may have little or no previous OT&E experience The Handbook provides detailed coverage on OT&E planning and management with special emphasis on measuring device operational effectiveness and suitability In accord with its objectives, the Handbook was prepared to serve as a supplement to Air Force Manual 55-43 'Management of Operational Test and Evaluation, but providing those specific additional evaluation concepts and techniques mecessary for aircrew training device test and evaluation GRA N82-28307# Strategic Air Command, Offutt AFB. Nebr Aircraft Engineering Div ALERT AIRCRAFT ROLL OVER CHOCKS Final Engineering Report John M Connolly 14 Aug 1981 53 p (AD-A107456. SAC/LGME-ER-P-372) Avail NTIS HC A04/MF A01 CSCL 01/5 The feasibility of restraining a parked alert aircraft with chocks which could be safely taxied over was studied Chocks were designed and then evaluated during SAC Giant Match II exercise The chocks successfully restrained a parked aircraft and allowed a heavy weight aircraft to safely taxi over when the chocks were placed on a rough surface Roll-over chock use was expanded command wide for B-52G and KC-135 alert aircraft except on icy surfaces Three ice gripping surface designs were evaluated All three designs performed successfully Author N82-28309# Naval Training Equipment Center, Orlando. Fla Advanced Simulation Concepts Lab COMPUTER PROGRAM FOR ANALYSIS OF SPHERICAL SCREEN DISTORTION Technical Report. Oct. 1980 - Feb. 1981 Richard C Hebb Mar 1982 71 p refs (AD-A113136, NAVTRAEQUIPC-IH-332) Avail NTIS HC A04/MF A01 CSCL 05/9 In visual simulation, the distortion of imagery in wide-angle display systems is a major concern Effective flight training requires that the imagery presented to a trainee provide a proper perspective view of his simulated environment without distor- tion Use of spherical screens (domes) introduces perspective and geometrical distortion into these wide-angle displays Use of video projection systems with Computer Image Generation (CIG) offers the options of raster shaping or computer remapping for distortion correction The method is to correct the imagery before projection in order to provide a non-distorted scene to a trainee This report is documentation of a computer program for analysis of the required raster correction for specific projector/ viewpoint positioning within a spherical screen The programs and report were initiated to provide input to the F-18 simulator (Device 2E7) being developed by Hughes Aircraft Author (GRA) N82-28310# Aeronautical Research Labs , Melbourne (Australia) PROGRAMS FOR THE TRANSONIC WIND TUNNEL DATA PROCESSING INSTALLATION. PART 8. PROGRAMS FOR PROCESSING DATA ON THE CENTRAL SITE COMPUTER B D Fairhe Sep 1980 32 p refs (AD-A112900, ARL/AERO-TM-324-Pt-8) Avail NTIS HC A03/MF A01 CSCL 09/2 Three programs which run on the central site computer (PDP-10) are described The first. PLT8 complements and extends the tunnel installation six-component force data plotting system The second, INTEG integrates aerofoil surface pressure measure- ments The third. PLTALL plots these surface pressure data Author (GRA) N82-28311# Aeronautical Research Labs . Melbourne (Australia) DESIGN BASIS FOR A NEW TRANSONIC WIND TUNNEL J B Willis and N Pollock Jan 1982 27 p refs (AD-A112899. ARL/Aero-TM-335. AR-002-326) Avail NTIS HC A03/MF A01 CSCL 14/2 The existing ARL Transonic Wind Tunnel, which is the largest such tunnel in Australia, has severely limited testing capabilities due to a low test Reynolds number and an inadequate test section size These deficiencies are'becoming more acute as military aircraft performance capabilities increase For current fighter aircraft, the ratio of tunnel test to flight Reynolds number is about 1 100 and the extrapolation of tunnel data tonfhght carries a high risk of serious error and for some conditions is not possible at all The small test section size limits the scale of the models which can be tested The difficulty of machining small models to the required accuracy produces excessive manufacturing times Moreover, it is not possible to incorporate remotely adjusted control surfaces These two factors severely restrict tunnel productivity Given adequate support, it should be possible to build and commission a suitable new wind tunnel in about five years, at a cost substantially less than that of a single military fighter aircraft GRA N82-28364# Messerschmitt-Boelkow-Blohm G m b H . Otto- brunn (West Germany) Information und Dokumentation CARBON FIBER REINFORCED COMPOSITE STRUCTURES PROTECTED WITH METAL SURFACES AGAINST LIGHT- NING STRIKE DAMAGE C M Heckert, H P Wentzel (Veremigte Flugtechnische Werke GmbH), and G Boes (Tech Univ . Hanover) 1982 9 p Presented at Intern Aerospace Conf on Lightning and Static Elec , Culham. England. 23-25 Mar 1982 (MB8-UD-340-82-O/E) Avail Issuing Activity Lightning protection for carbon fiber reinforced composite (CFC) structures, typical of parts mainly located on the surface of aircraft, was investigated Only direct structural, effects of a lightning strike on a component were considered As protective materials, flame sprayed aluminum, aluminum mesh, aluminum foil, and aluminum/glass hybrid fabrics were tested Three specimen geometries were studied (1) solid CFC plates 2 and 3 mm thick, (2) sandwich plates with CFC facing of different thickness and with different core material (aluminum and Nomex) 10 mm through, and (3) electrically bonded test specimen composed of a solid CFC plate and metal substructure The test rig for simulating lightning discharges is described Results consist of damage diagrams showing specimen type, applied electrical discharge, and damaged area on protective surface and composite structure Author (ESA) N82-28365# Messerschmitt-Boelkow-Blohm G m b H , Otto- brunn (West Germany) Information und Dokumentation DEVELOPMENT OF MATERIALS AND MANUFACTURING TECHNOLOGY OVER THE NEXT 20 YEARS: COMPOSITE MATERIALS [ENTWICKLUNG DER WERKSTOFF- UND FERTIGUNGSTECHNIK IN DEN NAECHSTEN 20 JAM REN - VERBUNDWERKSTOFFE] C M Heckert 1982 17 p In GERMAN Presented at Wehrtech Symp Entwicklung der Werkstoffe- u Fertigungstech in den naechsten 20 Jahren. Mannheim, West Germany, 17 Dec 1981. sponsored by Bundesakademie fuer Wehrverwaltung und Wehrtechmk. Mannheim, West Germany (MBB-UD-341-82-O) Avail Issuing Activity The development of reinforced plastics and their application in various manufacturing processes are reviewed The choice of CFRP or glass fiber reinforced plastic in military and com- mercial aircraft design is justified by higher specific strength and stiffness properties than alternative metals Other applica- tions are found in automobiles, railway cars, and helicopters Size and mass reduction in parts as well as production cost savings are mentioned Influence on manufacturing of component geometry (rod, plate, complex) is considered The interrelationship of manufacturing capability with composite materials development is stressed through examples from industry Author (ESA) N82 28462# Suntech. Inc Marcus Hook. Pa AN EXPLORATORY RESEARCH AND DEVELOPMENT PROGRAM LEADING TO SPECIFICATIONS FOR AVIATION TURBINE FUEL FROM WHOLE CRUDE SHALE OIL PART 1 PRELIMINARY PROCESS ANALYSES Interim Report, 2 Jan - 1 Jul. 1979 H E Reif. J P Schwedock and A Schneider Wright-Patterson AFB. Ohio AFWAL Sep 1981 48 p refs 3 Vol (Contract F33615-78-C-2024. AF Proj 3048) (AD-A112681 AFWAL-TR-81-2087-PI-1) Avail NTIS HC A03/MF A01 CSCL 21/4 Preliminary process analyses of three different technically feasible processing schemes proposed by SUN TECH, INC for converting 100.000 BPCD of raw Paraho shale oil into military turbine fuels was investigated Each processing scheme is based on very limited, but pertinent, data generated by SUN TECH plus literature sources The base processing scheme consists of severe hydrotreatmg followed by sulfunc acid extraction, the two alternate cases utilize moderate hydrotreatmg plus extraction for nitrogen removal and hydrocracking Screening-type process designs and costs estimates were prepared for each case using 527 N82-28463 the economic basis specified Results indicate that shale oil fuels refineries are more capital intensive than a comparable size petroleum refinery No attempt was made at optimization Author (GRA) N82 28463# Suntech, Inc . Marcus Hook. Pa AN E X P L O R A T O R Y RESEARCH AND DEVELOPMENT PROGRAM LEADING TO SPECIFICATIONS FOR AVIATION TURBINE FUEL FROM WHOLE CRUDE SHALE OIL. PART 2 PROCESS VARIABLE ANALYSES AND LABORA- TORY SAMPLE PRODUCTION Interim Report. Jul 1979 • 1 Nov. 1980 H E Reif. J P Schwedock. and A Schneider Wright-Patterson AFB. Ohio AFWAL Sep 1981 61 p refs 3 Vol (Contract F33615-78-C-2024. AF Proj 2480) (AD-A1 12682 AFWAL-TR-81-2087-PI-2) Avail NTIS HC A04/MF A01 CSCL 21/4 Pilot plant process data have been incorporated in three design bases for manufacturing military fuels from raw Occidental shale oil Processing schemes for 90.000 BPCD refineries to maximize either JP-4 JP-8 or to produce JP-4 plus other military fuels are presented The processing sequence comprises moderate severity hydrotreatmg. fractionation, anhydrous HCI extraction and hydrocarcking Plant capacities and product yields were not optimized Investments for the three refinery options considered are 1 5 to 2 0 times as much as a comparable size petroleum fuels refinery At maximum JP-4 or JP-8 production the yields are about 87 and 53 volume % of total refinery energy input, respectively Overall, refinery thermal efficiency is > or = 75% Inspection data are presented for five samples of specification aviation turbine fuels prepared from pilot plant operations GRA N82 28464# Suntech. Inc Marcus Hook Pa AN EXPLORATORY RESEARCH AND DEVELOPMENT PROGRAM LEADING TO SPECIFICATIONS FOR AVIATION TURBINE FUEL FROM WHOLE CRUDE SHALE OIL. PART 3: PRODUCTION OF SPECIFICATION OF JP-4 FUEL FROM GEOKINETICS SHALE OIL Interim Report. 1 Jan - 1 Apr 1980 H E Reif, J P Schwedock. and A Schneider Wright-Patterson AFB Ohio AFWAL Oct' 1981 45 p refs 3 Vol (Contract F33615-78-C-2024. AF Proj 2480) (AD-A1 12683, AFWAL-TR-81-2087-Pt-3) Avail NTIS HC A03/MF A01 CSCL 21/4 270 Barrels of specification JP-4 jet fuel were produced by hydrorefinmg 890 barrels of raw Geokmetics shale oil under severe operating conditions in a continuous process development unit On a once thru basis the yield of JP-4 off the hydrotreater was about 35 volume % of ^he feed Preliminary estimates of plant investments and economics indicate that for the combination severe hydrorefinmg and hydrocrackmg an 85 volume % yield can be attained based on total refinery energy input Capital investments and manufacturing costs do not appear to be excessive for a shale oil refinery GRA N82-28470# California Umv . Livermore Lawrence Livermore Lab LABORATORY-SCALE SIMULATION OF UNDERGROUND COAL GASIFICATION EXPERIMENT AND THEORY J R Creighton and C B Thorsness 28 Aug 1981 26 p refs Presented at the Western States Sect Meeting of the Combust Inst Tempe. Ariz . 19-20 Oct 1981 (Contract W-7405-eng-48) (DE82-001063. UCRL-86473. CONF-811041-2) Avail NTIS HC A03/MF A01 Laboratory-scale experiments simulating underground coal gasification are described A 1 cm borehole is drilled through a block of coal which is cut to fit in a 55 gallon oil drum Inlet gas may be air or oxygen/steam mixture at various ratios The blocks are burned for a period of several hours at a prescribed flow schedule, with appropriate instrumentation Gas quality is found to be relatively independent of coal type for the range of sub-bituminous coals tested After the burn the blocks of coal are cut open to examine the cavity A mathematical modeling effort supports these experiments The models are restricted to pure carbon, to simplify the chemistry in the model When plug flow is assumed in the cavity the model predicts reasonable cavity shape downstream, but an incorrect shape upstream When aerodynamic flow including viscosity and vortex formation, is calculated in the cavity reasonable cavity shapes are obtained DOE N82-28486# Veremigte Flugtechnische Werke G m b H . Bremen (West Germany) Materials and Processes Development Dept ADVANCED CASTING: TODAY AND TOMORROW Dietmar Mietrach 1982 20 p refs Presented at AGARD Meeting on Adv Casting Technol. Brussels 4-9 Apr 1982 Avail NTIS HC A02/MF A01 The state of aluminum casting technology in terms of processes, component sizes design and material-scientific data as well as mechanical characteristics was established during visits to foundries in the USA. Canada. France Italy. Great Britain and the Federal Republic of Germany Components of the primary structure of Tornado and ALPHA aircraft, (pylon, intake floor) classified according to the degree of difficulty during casting, were used to compare existing designs (riveted sheet metal and machined parts) and cast versions with regard to cost reduction and technical reliability Visual inspection, dimensional checks, chemical composition analysis, penetrant tests X-ray tests, metallographic investigations, and tensile tests were carried out Cost savings of 25% and weight savings of 20% can be achieved by using castings Author (ESA) N82-28523# TRW Defense and Space Systems Group. Redondo Beach, Calif MULTIFUNCTION MULTIBAND AIRBORNE RADIO AR- CHITECTURE STUDY Final Report. Apr. 1978 - Jan 1980 L N Ma. S K Ogi, M Y Huang. L L Bodnar, and P Martin Wright-Patterson AFB. Ohio AFWAL Jan 1982 379 p refs (Contract F33615-77-C-1172. AF Proj 2003) (AD-A114427, AFWAL-TR-81-1113) Avail NTIS HC A17/MF A01 CSCL 17/2 The demands of modern military avionic communication, radio navigation, and cooperative identification (CNI) equipment has been greatly expanded as the result of the need for antijam (AJ). low probability of intercept (LPI), higher navigation accuracy, and increased volume of information transfer These demands are verified in programs such as GPS. JTIDS, SEEK TALK, SINCGARS and AFSAT I and II The cost of this additional capability has severely hampered the ability of the Government to procure new CNI systems and equipment with desired performance capabilities The problem is further compounded by the lack of available space in the tactical aircraft, the transition of new equipment into the inventory, and the retention of many current systems The multifunction multiband airborne radio system (MFBARS) program is formulated to explore the feasibility of producing a modern CNI system at an affordable life cycle cost (LCC) and within real estate requirements A cost effective system approach was developed that revolved around high technology RF-LSI analog components that are in the development stage high speed digital pre-processor elements and a programmable signal processor all under control of a host processor configuration This design trades the ultimate gam in volume, weight and life cycle cost against a reasonable risk for the mid 1980's development Author (GRA) N82-28552# Boeing Aerospace Co. Seattle. Wash FEASIBILITY STUDY OF A 270V dc FLAT CABLE AIRCRAFT ELECTRICAL POWER DISTRIBUTED SYSTEM Final Report. Dec. 1980 - Jan. 1982 M J Musga and R J Rmehart Jan 1982 272 p refs (Contract N62269-81-C-0231) (AD-A114026, D182-10816-1. NADC-82023-60) Avail NTIS HC A12/MF A01 CSCL 10/2 This report documents the efforts of a one man-year feasibility study to evaluate the usage of flat conductors in place of conventional round wires for a 270 volt direct current aircraft power distribution system This study consisted of designing electrically equivalent power distribution harnesses in flat conductor configurations for a currently operational military aircraft Harness designs were established for installation in aircraft airframes which are (1) All metal, or (2) All composite, or (3) a mixture of both Flat cables have greater surface areas for heat transfer allowing higher current densities and therefore lighter weight conductors, than with round wires Flat cables are less susceptible to electromagnetic effects However, these positive factors are partially offset by installation and maintenance difficulties This study concludes that the extent of these difficulties can be adequately limited with appropriate modification to present installation and maintenance practices A comparative analysis of the flat and the round conductor power distribution harnesses was made for weight, cost, maintenance and reliability The knowledge gained from the design and comparative analysis 528 N82-28715 phases was used to generate design criteria for flat power cable harnesses and to identify and prioritize flat cable harness components and associated production tooling which require development GRA N82-28571# Aeronautical Research Inst of Sweden, Stockholm MEASURING THE FLOW PROPERTIES OF SLOTTED TEST-SECTION WALLS Sune B Berndt May 1982 15 p refs (FFA-135) Avail NTIS HC A02/MF A01 By measuring pressure distributions at two levels near a slotted wall it is possible to deduce simultaneous values of normal and longitudinal velocities Such measurements require, for their proper interpretation, a basic understanding of the flow in the neighborhood of the wall An analysis of the problems involved is provided , Author N82-28624# Rose Engineering and Research, Inc , Incline Village, Nev NEARFIELD AERODYNAMICS AND OPTICAL PROPAGA- TION CHARACTERISTICS OF A LARGE-SCALE TURRET MODEL Final Report William C Rose. James E Craig (Spectron Development Lab, Inc), and K R Raman (Raman Aeronautics, Inc) Kirtland AFB. N Mex AFWL Feb 1982 100 p refs (Contract F29601-79-C-0011. AF Proj 317J) (AD-A113910. AFWL-TR-81-28) Avail NTIS HC A05/MF A01 CSCL 20/6 Measurements of the unsteady flow field affecting optical propagation quality have been made with both aerodynamic and direct optical instrumentation Properties affecting degradation of coherent radiation beams propagated from within the turret have been investigated These properties include both the magnitude and scale sizes of the fluctuating index-of-refraction field present in the turbulent shear layers and separation regions of the turret flow field Direct optical degradation information was obtained by holographic mterferometry and quantified through techniques presented here Aerodynamic measurements were made with hot-wire anemometry and multiple-port probes Comparisons between the aerodynamically and optically deduced data are presented These data can be used directly to estimate trends in expected loss of optical quality of a coherent beam for various flight speeds, altitudes, wavelengths and azimuthal turret angles More data are now available for estimating the effects of unsteady aerodynamic flow fields on optical propagation quality Data were obtained for Reynolds numbers near those occurring at full-scale flight conditions over a range of Mach number from 0 55 to 0 75 Investigation results generally agree with those obtained previously on smaller scale models and indicate that severe optical degradation can be present at aft-looking azimuth angles Author (GRA) N82-28643*// National Aeronautics and Space Administration Lewis Research Center. Cleveland. Ohio RELIABILITY MODEL FOR PLANETARY GEAR Michael Savage (Akron Univ ). Charles A Paridon (Hewlett Packard Co. Sunnyvale. California), and John J Coy (Army Aviation Research and Development Command. Cleveland Ohio) _ 1982 22 p refs Proposed for Presentation at Design Engr Tech Conf Washington DC. 12-15 Sep 1982 sponsored by ASM E Prepared in cooperation with Army Aviation Research and Development Command (NASA-TM-82859 NAS 11582859 AVRADCOM-TR-82-C-6) Avail NTIS HC A02/MF A01 CSCL 131 A reliability model is presented for planetary gear trains in which the ring gear is fixed, the Sun gear is the input, and the planet arm is the output The input and output shafts are coaxial and the input and output torques are assumed to be coaxial with these shafts Thrust and side loading are neglected This type of gear train is commonly used in mam rotor transmissions for helicopters and in other applications which require high reductions in speed The reliability model is based on the Weibull distribution of the individual reliabilities of the transmission components The transmission's basic dynamic capacity is defined as the input torque which may be applied for one million input rotations of the Sun gear Load and life are related by a power law The load life exponent and basic dynamic capacity are developed as functions of the component capacities Author N82-28644*# National Aeronautics and Space Administration Lewis Research Center Cleveland Ohio ADVANCES IN HIGH-SPEED ROLLING-ELEMENT BEAR- INGS Erwm V Zaretsky 1982 29 p refs Presented at the 16th Ann Israel Conf on Mechan Engr Haifa Israel 12-14 Jul 1982 sponsored by Technion - Israel Inst of Tech (NASA-TM-82910 E-1295 NAS 11582910) Avail NTIS HC A03/MF A01 CSCL 131 Aircraft engine and transmission rolling-element bearing state-of-the-art is summarized Author N82-28676# Alabama Univ Huntsville Dept of Mechanical Engineering RECENT DEVELOPMENTS IN HYGROTHERMOVISCOELAS- TIC ANALYSIS OF COMPOSITES T J Chung In Shock and Vibration Information Center The Shock and Vibration Digest Vol 14. No 4 Apr 1982 p 33-40 refs (For primary document see N82-28673 19-39) Avail SVIC. Code 5804. Naval Research Lab Washington D C 20375. $20 00/set CSCL 20/1 1 Constitutive theories of hygrothermomechanical behavior of viscoelastic composites are reviewed Author N82-28685# National Aerospace Lab Amsterdam (Netherlands) Structures and Materials Div PREDICTION OF FATIGUE C R A C K GROWTH RATES UNDER VARIABLE LOADING USING A SIMPLE CRACK CLOSURE MODEL A U deKonmg and H H vanderLmden Apr 1980 45 p refs Presented at 11th ICAF Symp Noordwi|kerhout, Netherlands 20-22 May 1981 (Contracts NIVR-1777 NIVR-1822, NIVR-1823) (NLR-MP-81023-U) Avail NTIS HC A03/MF A01 A model which predicts fatigue crack growth rates in aluminum alloys subjected to flight service loading is presented The model is based on an approximate description of the crack opening behavior and was applied successfully in an analysis of effects of crack growth acceleration and retardation observed experimentally under variable amplitude loading The model describes effects of the plane strain to plane stress transition and of relatively high overloads on crack growth rate of the crack Author (ESA) N82-28690*# National Aeronautics and Space Administration Wallops Flight Center, Wallops Island Va BASELINE MONITORING USING A I R C R A F T LASER RANGING W B Krabill. F E Hoge and C F Martin Jun 1982 28 p refs(NASA-TM-73298 NAS 11573298) Avail NTIS HC A03/MF A01 CSCL 08B The use of aircraft laser ranging for the determination of baselines between ground based retroreflectors was investigated via simulations and with tests at Wallops Flight Center using the Airborne Oceanographic Lidar (AOL) on the Wallops C-54 aircraft ranging to a reflector array deployed around one of the Wallops runways The aircraft altitude and reflector spacing were chosen on the basis of scaled down modeling of spacecraft tracking from 1000 km of reflectors separated by some 52 km or of high altitude (10 km) aircraft tracking of reflectors separated by some 500 m Aircraft altitudes flown for different passes across the runway reflector array varied from 800 m to 1350 m. with 32 reflectors deployed over an approximately 300 m x 500 m ground pattern The AOL transmitted 400 pulses/sec with a scan rate of 5/sec in a near circular pattern so that the . majority of the pulses were reflected by the runway surface or its environs rather than by retroreflectors The return pulse characteristics clearly showed the high reflectivity of portions of the runway with several returns indistinguishable in amplitude from reflector returns For each pass across the reflector field typically six to ten reflector hits were identified consistent with that predicted by simulations and the observed transmitted elliptical pulse size Author N82-28715*# National Aeronautics and Space Administration Goddard Space Flight Center Greenbelt Md SCANNER IMAGING SYSTEMS. AIRCRAFT Stephen G Ungar In JPL Proc of the NASA Workshop on Registration and Rectification 1 Jun 1982 p 138-152 (For primary document see N82-28699 19-43) Avail NTIS HC A23/MF A01 CSCL 08B 529 N82-28841 The causes and effects of distortion in aircraft scanner data are reviewed and an approach to reduce distortions by modelling the effect of aircraft motion on the scanner scene is discussed With the advent of advanced satellite borne scanner systems, the geometric and radiometnc correction of aircraft scanner data has become increasingly important Corrections are needed to reliably simulate observations obtained by such systems for purposes of evaluation It is found that if sufficient navigational information is available, aircraft scanner coordinates may be related very precisely to plammetnc ground coordinates However, the potential for a multivalue remapping transformation (i e . scan lines crossing each other) adds an inherent uncertainty, to any radiometnc resampling scheme which is dependent on the precise geometry of the scan and ground pattern E A K N82-28841# Aerospace Medical Research Labs. Wright- Patterson AFB Ohio Biodynamics and Bioengmeenng Div FIELD STUDIES OF THE AIR FORCE PROCEDURES (NOISECHECK) FOR MEASURING COMMUNITY NOISE EXPOSURE FROM AIRCRAFT OPERATIONS Final Report R A Lee Mar 1982 130 p (AF Pro) 7231) (AD-A113672. AFAMRL-TR-82-12) Avail NTIS HC A07/MF A01 CSCL 20/1 This report describes the results of noise measurements at Laughlm AFB and Homestead AFB to field test the NOISECHECK equipment and procedures developed' under contract by Bolt. Beranek and Newman, Inc and Digital Acoustics Inc NOISE- CHECK is the equipment and procedures used by the Air Force to spot check or validate the long term noise exposure predicted by NOISEMAP the Air Force computer program for predicting community noise exposure' from aircraft operations The total noise exposure level at a specified location has an uncertainty associated with it whether the level is predicted or measured The purpose of NOISECHECK is to determine the total noise exposure in terms of the Day-Night Level (DNL) metric for a specified ground location from direct measurements NOISEMAP predicts DNL values for yearly-averaged 'busy days' aircraft operations Therefore, the direct DNL measurements need to be normalized to this busy day DNL The NOISECHECK Procedures lead you through these normalizations in a straightforward step-by-step method The results of the Laughlm and Homestead tests show that, with the proper data collection, the NOISECHECK procedures can validate the long-term noise exposure and explain any differences between the NOISEMAP predicted DNL values and the short term measurement DNL values Author (GRA) N82-28842# California Umv . Riverside Statewide Air Pollution Research Center ATMOSPHERIC CHEMISTRY OF HYDROCARBON FUELS. VOLUME 2 OUTDOOR CHAMBER DATA TABULATIONS. PART 1 Final Report. Mar 1980 - Sep 1981 William P L Carter. Paul S Ripley. Cecil G Smith, and James N Pitts, Jr Tyndall AFB, Fla AF Engineering and Services Center Nov 1981 336 p 2 Vol (Contract F08635-80-C-0086. AF Proj 1900) ( A D - A 1 13665 AFESC/ESL-TR-81-53-V-2-P-1) Avail NTIS HC A15/MF A01 CSCL 04/1 A total of 132 single- and multi-day outdoor environmental chamber experiments were conducted, involving nine different aviation and automotive fuels These included the petroleum- derived JP-4 and JP-8 military aviation fuels their shale-oil derived analogues, unleaded gasoline, diesel No 2 fuel, and the experimental high-energy cruise-missile fuels JP-10 RJ-4. and RJ-5 The program was conducted to assess the potential of these fuels to adversely affect air quality Author N82 28881 *# Tennessee Umv Space Inst Tullahoma ANALYSIS OF VIBRATION INDUCED ERROR IN TURBU- LENCE VELOCITY MEASUREMENTS FROM AN AIRCRAFT WING TIP BOOM Final Report Safwan H Akkari and Walter Frost Washington NASA Jun 1982 77 p refs (Contract NAS8-34627) (NASA-CR-3571 NAS 1263571) Avail NTIS HC A05/MF A01 CSCL 048 The effect of rolling motion of a wing on the magnitude of error induced due to the wing vibration when measuring atmospheric turbulence with a wind probe mounted on the wtng tip was investigated The wing considered had characteristics similar to that of a B-57 Cambera aircraft and Von Karman s cross spectrum function was used to estimate the cross- correlation of atmospheric turbulence Although the error calculated was found to be less than that calculated when only elastic bendmgs and vertical motions of the wing are considered, it is still relatively large in the frequency s range close to the natural frequencies of the wing Therefore it is concluded that accelerometers mounted on the wing tip are needed to correct for this error, or the atmospheric velocity data must be appropriately filtered Author N82-29022*# Research Triangle Inst. Research Triangle Park, N C Systems and Measurements Div PROBLEMS RELATED TO THE INTEGRATION OF FAULT TOLERANT AIRCRAFT ELECTRONIC SYSTEMS J A Bannister, V Adlakha, K Tnyedi. and T A Alspaugh, Jr Jun 1982 167 p refs (Contract NAS1-16489) (NASA-CR-165926, NAS 126165926. RTI/2094/02-02F) Avail NTIS HC A08/MF A01 CSCL 09B Problems related to the design of the hardware for an integrated aircraft electronic system are considered Taxonomies of concurrent systems are reviewed and a new taxonomy is proposed.An informal methodology intended to identify feasible regions of the taxonomic design space is described Specific tools are recommended for use in the methodology Based on the methodology, a preliminary strawman integrated fault tolerant aircraft electronic system is proposed Next, problems related to the programming and control of megrated aircraft electronic systems are discussed Issues of system resource management, including the scheduling and allocation of real time periodic tasks in a multiprocessor environment, are treated in detail The role of software design in integrated fault tolerant aircraft electronic systems is discussed Conclusions and recommendations for further work are included M G N82-29111*jj( Stanford Univ. Calif Joint Inst for Aeronautics and Acoustics THE EFFECT OF BARRIERS ON WAVE PROPAGATION PHENOMENA WITH APPLICATION FOR AIRCRAFT NOISE SHIELDING C V M Mgana and l-Dee Chang May 1982 142 p refs (Contract NCC2-76) (NASA-CR-169128. NAS 126169128) Avail NTIS HC A07/MF A01 CSCL 20A The frequency spectrum was divided into high and low frequency regimes and two separate methods were developed and applied to account for physical factors associated with flight conditions For long wave propagation the acoustic filed due to a point source near a solid obstacle was treated in terms of an inner region which where the fluid motion is essentially incompres- sible, and an outer region which is a linear acoustic field generated by hydrodynamic disturbances in the inner region This method was applied to a case of a finite slotted plate modelled to represent a wing extended flap for both stationary and moving media Ray acoustics, the Kirchhoff integral formulation, and the stationary phase approximation were combined to study short wave length propagation in many limiting cases as well as in the case of a semi-infinite plate in a uniform flow velocity with a point source above the plate and embedded in a different flow velocity to simulate an engine exhaust |et stream surround- ing the source A R H N82-29116# Technische Physische Dienst TNO-TH, Delft (Netherlands) USE OF THE CAVITATION TUNNEL AT THE DUTCH NAVAL EXPERIMENT STATION (NSP). WAGENINGEN FOR THE DETERMINATION OF THE ACOUSTIC SOURCE STRENGTH OF PROPELLER CAVITATION [HET GEBRUIK VAN DE CAVITATIETUNNELVAN HET NSP TE WAGENINGEN VOOR DE BEPALING VAN DE AKOESTISCHE BRONSTERKTE VAN SCHROEFCAVITATIE] K Verhulst 18 Aug 1981 44 p refs In DUTCH (Contract A72/KM/007) (TPD-908-720 TDCK-75536) Avail NTIS HC A03/MF A01 Experiments were performed using a five blade model propeller in order to investigate the possibilities of using the large NSP .cavitation tunnel in the acoustical study of propeller cavitation The influence of the hydrodynamic characteristics in the tunnel on the sound transmission to the tunnel wall was investigated The transfer functions fluctuate strongly, even at a given water velocity or static pressure, probably due to poor 530 N82-29275 acoustic damping in the tunnel circuit For a turning propeller the acoustic response of the tunnel wall due to propeller cavitation is very stable since the degree of turbulence in the water and thus the absorption, are very high Author (ESA) N8229118# Max-Planck-lnstitut fuer Stroemungsforschung, Goettmgen (West Germany) SOME COMMENTS ON THE PREDICTION OF FORWARD FLIGHT EFFECTS ON JET NOISE Frank Obermeier Dec 1981 37 p refs (MPIS-20/1981 ISSN-0436-1199) Avail NTIS HC A03/MF A01 Fachmformationszentrum. Karlsruhe. West Germany DM 8.55 How aeroacoustic sound generation in turbulent jet flow is affected by a coflowing stream is considered Experiment shows that simply allowing for Doppler effects, applied to the sound field of a static jet which is assumed to be known, does not yield convincing results The effects of a coaxial stream on the aerodynamics of |et flow, i e , the effects on its characteristic length and velocity, found experimentally, are critically reviewed through the literature Results lead to a prediction scheme for m-fhght effects on jet noise A comparison of this method with test data exhibits good agreement Author (ESA) N82-29261jf Federal Aviation Administration Washington DC Planning Analysis Div FAA AVIATION FORECASTS-FISCAL YEARS 1982-1993 Feb 1982 72 p (AD-A1 14696 FAA-APO-82-2) Avail NTIS HC A04/MF A01 CSCL 01/2 This report contains the Fiscal Years 1982 to 1993 Federal Aviation Administration (FAA) forecasts of aviation activity at FAA facilities These include airports with FAA control towers air route traffic control centers, and flight service stations Detailed forecasts were made for the four major users of the national aviation system air carriers, air taxi/commuters, general aviation and the military The forecasts have been prepared to meet the budget and planning needs of the constituent units of the FAA and to provide information that can be used by state and local authorities by the aviation industry and the general public GRA N82-29263# Aeronautical Research Inst of Sweden Stockholm Aerodynamics Dept ON EMBEDDED FLOW CHARACTERISTICS OF SHARP EDGED RECTANGULAR WINGS Erik S Larson 21 Apr 1982 19 p refs Backup Document for AIAA Synoptic scheduled foi publication in the Journal of Aircraft Feb or Mar 1983 (Log-C4712) Avail N1IS HC A02/MF A01 The semiempmcal analytic expressions for steady, symmetric flow characteristics on thin rectangular wings at transonic speed are investigated Semiempmcal expressions representing aerody- namic characteristics of sharp edged rectangular wings are reported The basic coefficients correlated very well with panel method results for Mach number of the free stream < or = 1 the intended domain of applicability S L N82-29267*# National Aeronautics and Space Administration Ames Research Center, Moffett Field, Calif AERODYNAMICS OF AN AIRFOIL WITH A JET ISSUING FROM ITS SURFACE D A Tavella and K Karamcheti May 1982 93 p refs (Contract NCC2-74) (NASA-TM-84825 NAS 11584825 SU-JIAA-TR-44) Avail NTIS HC A05/MF A01 CSCL 01A A simple, two dimensional, incompressible and inviscid model for the problem posed by a two dimensional wing with a jet issuing from its lower surface is considered and a parametric analysis is carried out to observe how the aerodynamic characteris- tics depend on the different parameter' The mathematical problem constitutes a boundary value problem where the position of part of the boundary is not known a priori A nonlinear optimization approach was used to solve the problem, and the analysis reveals interesting characteristics that may help to better' understand the physics involved in more complex situations in connection with high lift systems Author N82-29268*jff National Aeronautics and Space Administration Ames Research Center, Moffett Field. Calif AIRCRAFT GEOMETRY VERIFICATION WITH ENHANCED COMPUTER GENERATED DISPLAYS J V Cozzolongo Jun 1982 13 p refs (NASA-TM-84254. NAS 11584254) Avail NTIS HC A02/MF A01 CSCL01A A method for visual verification of aerodynamic geometries using computer generated, color shaded images is described The mathematical models representing aircraft geometries are created for use in theoretical aerodynamic analyses and in computer aided manufacturing The aerodynamic shapes are defined using parametric bi-cubic splmed patches This mathemati- cal representation is then used as input to an algorithm that generates a color shaded image of the geometry A'discussion of the techniques used in the mathematical representation of the geometry and in the rendering of the color shaded display is presented The results include examples of color shaded displays, which are contrasted with wire frame type displays The examples also show the use of mapped surface pressures in terms of color shaded images of V/STOL fighter/at tack aircraft and advanced turboprop aircraft Author N82-29271*# Boeing Vertol Co, Philadelphia, Pa INVESTIGATION OF A ROTOR SYSTEM INCORPORATING A CONSTANT LIFT TIP Final Contractor Report M A McVeigh, H Rosenstem. K Bartie and F J McHugh Oct 1981 326 p refs (Contract NAS2-10769) (NASA-CR-166261. NAS 126166261) Avail NTIS HC A15/MF A01 CSCL 01A A wind tunnel test of a 16 8 ft model of a rotor having passively controlled pivotable tips is described Performance and vibratory hub load data are presented which compare the performance of the rotor with the tips free and fixed. A brief analysis of the experimental findings is included S L N82-29274# Federal Aviation Administration Washington. D C Office of Aviation Medicine FLIGHT ATTENDANT INJURIES 1971-1976 Donell W Pollard. Earl D Folk, and Richard F Chandler Jan 1982 60 p refs (AD-A1 14909 FAA-AM-82-8) Avail NTIS HC A04/MF A01 CSCL 01/2 Data from 206 reports of 377 flight attendant injuries occurring from 1971 through 1976 are summarized These data were obtained from the Cabin Safety Data Bank of the Civil Aeromedical Institute, and are based on Federal Aviation Administration and National Transportation Safety Board accident/incident reports Information relating to the severity and location of the injury is provided when available from original reports Data relating to the flight condition and location in the aircraft where the injury occurred are provided Summaries of each reported injury are included in the appendices Author (GRA) N82-29275# Federal Aviation Administration. Washington. D C Office of Aviation Medicine CRASHWORTHINESS STUDIES CABIN. SEAT. RE- STRAINT. AND INJURY FINDINGS IN SELECTED GENERAL AVIATION ACCIDENTS William R Kirkham. S Marlene Wicks and Donald Lee Lowrey Mar 1982 24 p refs (AD-A114878, FAA-AM-82-7) Avail NTIS HC A02/MF A01 CSCL 01/2 This report reviews 47 survivable or partly survivable accidents investigated since 1973 by personnel from the Civil Aeromedical Institute The accidents were reviewed for a number of features of crashworthmess and, m particular for injuries to occupants in relation to the severity of the impact and the performance of cabin and restraint systems Opinions were rendered by trained crash injury investigators as to the role or expected role in seats and upper torso restraints in adding to or lessening the injuries The data support the general concepts that nonoccupiable portions of the aircraft receive greater physical damage than occupiable areas The greatest damage to the occupiable area is to the forward portion of cockpit/cabin and the occupants have a greater chance of survival if the cockpit/cabin remains reasonably intact Occupants seated forward in the cockpit/cabin receive greater injuries than those seated more rearward Further the findings suggest tha seat placement or seat failure to one degree or another intensified injuries (as compared to more optimum crashworthy seats) to occupants in at least 531 N82-29276 30 percent of the accidents reviewed Upper torso restraints, in the few instances used, were beneficial, and had they been used by all occupants, would have significantly reduced the injuries The report discusses the relation of the occupant to the seat and restraint system and the apparent benefit to be derived from a well-designed impact attenuating seat and. in particular, use of an upper torso restraint Author (GRA) N82-29276# Federal Aviation Administration. Atlantic City, NJ REDUCTION AND ANALYSIS OF MODE C ALTITUDE DATA COLLECTED AT HIGH ALTITUDES OVER THE CONTINEN- TAL UNITED STATES Final Report, Sep. 1977 - Apr. 1978 Robert Rigolizzo Mar 1982 101 p refs (AD-A114655. DOT/FAA/CT-81/53. DOT/FAA/EM-82/9) Avail NTIS HC A06/MF A01 CSCL 01/2 This report describes the reduction and analysis of mode C altitude data collected over the en route centers of Cleveland. Ohio. Memphis. Tennessee, and Albuquerque. New Mexico The data were gathered under the aegis of the separation standards program primarily for the study of lateral navigation performance over the continental United States at high altitudes This study provides a procedure for estimating the vertical flight technical error as evidenced from mode C altitude data recorded at the en route centers It does not account for basic altimeter system error or flight technical error biases and/or fluctuations that are not observable in the ground-derived mode C reported altitude The data are fitted to six different analytical distributional forms The effect that data quantization has on the estimation of the parameters of the distributions is examined Then statistical tests are performed to evaluate the appropriateness of each distributional model in representing the histogram of the mode C deviations A preliminary analysis is conducted to investigate the association between mode C altitude and aircraft environmen- tal performance characteristics commonly utilized in evaluating separation criteria as well as identifying aircraft attributes that are of major interest when evaluating vertical flight technical error Author (GRA) N82-29277# Clemson Univ. SC Dept of Industrial Management MAXIMIZING SOUTH CAROLINA'S AVIATION RE- SOURCES IDENTIFYING POTENTIALLY PROFITABLE COMMUTER AIRLINE ROUTES. VOLUME 2 Clinton H Whitehurst. Jr. Mark A McKnew. Michael W Broadway, and Gayle H Taylor Oct 1981 168 p refs (Grant EDA-04-06-03042-40) (PB82-139353. EDA-81-0132) Avail NTIS HC A08/MF A01 CSCL 01 B The commuter airline routes within South Carolina were analyzed It is concluded there are. in fact, a number of potentially profitable commuter airline routes between communities within South Carolina and interstate routes tying some communities in the State to medium and large hub airports There is however, still work to be done As rnmrnumties grow in size and should air service to the State by trunk carriers decline further, it would be well worth it for a community to reevaluate its potential to support commuter service in terms of the profitability criteria outlined in this study GRA N82-29278# National Transportation Safety Board. Washington. D C Bureau of Technology ANNUAL REVIEW OF AIRCRAFT ACCIDENT DATA. US GENERAL AVIATION CALENDAR YEAR 1979 5 Nov 1981 213 p (PB82-136250 NTSB-ARG-81-1) Avail NTIS HC A10/MF A01 CSCL01B Aircraft accidents which occurred in U S general aviation operations during the calendar year 1979 are summarized It includes an analysis of accident data involving an overview, types of accidents, accidental causal factors, kind of flying, and conclusions a statistical compilation of accident information presented in the form of accident and rate tables, analytic tables, injury tables and cause/factor tables These statistical data are divided into sections pertaining to all operations, small fixed-wing aircraft, large fixed-wing aircraft, rotorcraft. gliders, and collisions between aircraft In 1979, there were 4,023 total general aviation accidents. 678 of which were fatal Included in the total number of accidents are 40 collisions between aircraft Author N82-29279# Advisory Group for Aerospace Research and Development, Neuilly-Sur-Seme (France) AIRCRAFT FIRE SAFETY May 1982 174 p refs Presented at AGARD Lecture Series, Oslo. 7-8 Jun 1982 and London. 10-11 Jun 1982 and Washington, 15-16 Jun 1982 (AGARD-LS-123. ISBN-92-835-1424-6) Avail NTIS HC A09/MF A01 Progress in aerospace science and technology, especially pertaining to aircraft safety was reported The goals of the international organization are to strengthen common defense posture, improve international cooperation in research and development, provide scientific and technical advance to NATO in aerospace R&D. increase scientific and technical potential and recommend effective use of R&D capabilities The following topics are discussed aircraft fire mishap experience/crash fire scenario quantitation. human response to fire aviation fuels, future outlook and impact on aircraft fire threat, fuel system protection methods, fireworthmess of transport aircraft interior systems, the develop- ment and application of a full scale wide body test article to study the behavior of interior materials during a postcrash fuel fire, aircraft postcrash fire reduction/survivability enhancement from a manufacturer's viewpoint, and aircraft postcrash fire fighting/rescue For individual titles, see N82-29280 through N82-29287 N82-29280# Federal Aviation Administration. Washington. D C Engineering Analysis Branch AIRCRAFT FIRE MISHAP EXPERIENCE/CRASH FIRE SCENARIO QUANTITATION Thomas G Horeff In AGARD Aircraft Fire Safety May 1982 6 p refs (For primary document see N82-29279 20-03) Avail NTIS HC A09/MF A01 Civil and military turbine aircraft accidents were reviewed It was confirmed that the major postcrash fire hazard was caused by ignition of fuel released from wing separation failured during impact survivable accidents General scenarios for postcrash fire hazards are described and heat flux levels and cabin airflow rates based on fuselage postcrash fire tests are suggested Fire fatalities to fire tests are suggested Fire fatalities to fire scenarios and fire experience data base through 1979 are related It is concluded that the reduction of postcrash fire gives the greatest potential for improved crashworthmess and increased occupant survivability E A K N82-29281| Army Aeromedical Research Lab, Fort Rucker, Ala HUMAN RESPONSE TO FIRE Stanley C Knapp and Francis S Knox, III In AGARD Aircraft Fire Safety May 1982 19 p (For primary document see N82-29279 20-03) Avail NTIS HC A09/MF A01 Human survival in aircraft fire was investigated Aircraft fires and human survival in thermophysical dimensions and aircraft fire properties, chemical and toxic nature of fibres, the concept of worst credible environment, and survival time dimension derived from ground and airborne fire suppression are discussed The epidemiology of human fire morbidity and mortality are divided into (1) no personal protection, no prevention of fire. (2) inadequate protection, no prevention of fire and (3) prevention of fire and good protection Assessment techniques to select fabric for protective clothing are examined Physical and biomedical bases to formulated strategies for the development of aircraft fire prevention and personal protection which leads to increased human survival is constructed E A K N82-29282# Air Force Wright Aeronautical Labs, Wright- Patterson AFB. Ohio Aero Propulsion Lab AVIATION FUELS-FUTURE OUTLOOK AND IMPACT ON AIRCRAFT FIRE THREAT A V Churchill In AGARD Aircraft Fire Safety May 1982 17 p refs (For primary document see N82-29279 20-03) Avail NTIS HC A09/MF A01 The properties of aviation turbine fuels with respect to aircraft fire safety are described It is indicated that projections of the availability of petroleum crudes specifications for aviation turbine fuels may have to be modified to use fuels produced from shale oil. heavy oils and coal Projections of the chemical and physical properties of future aviation fuels produced from these alternative sources are discussed and compared with present fuels Progress on programs to devejop fire safe fuels through the use of antimistmg additives is also described E A K 532 N82-29291 N82-29283# Royal Aircraf t Establishment Farnborough (England) Engineering Physics Dept FUEL SYSTEM PROTECTION METHODS H W G Wyeth In AGARD Aircraft Fire Safety May 1982 16 o refs (For primary document see N82-29279 20-03) Avail NTIS HC A09/MF A01 A fuel system protection equipment for military aircraft and helicopters, to reduce fires and explosions which occur under combat conditions was developed Equipments are available for fitment to civil transport for survivabihty enhancement It is recommended that aircraft fire safety and crash resistance in the initial design and appropriate safety precautions taken to minimize the risk of fire and explosion both in flight and on the ground should be considered It is concluded that fuel containment systems and antimistmg fuels can reduce dynamic fuel spillage and improve occupant survivabihty in postcrash fire E A K N82-29284*# National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif FIREWORTHINESS OF TRANSPORT AIRCRAFT INTERIOR SYSTEMS John A Parker and D A Kourtides In AGARD Aircraft Fire Safety May 1982 17 p refs (For primary document see N82-29279 20-03) Avail NTIS HC A09/MF A01 The fire worthiness of air transport interiors was evaluated The effect of interior systems on the survival'of passengers and crew in an uncontrolled transport aircraft fire is addressed Modification of aircraft interior subsystem components which provide improvements in aircraft fire safety are examined Three specific subsystem components, interior panels, seats and windows offer the most immediate and highest payoff by modifying interior materials of existing aircrafts It is shown that the new materials modifications reduce the fire hazards because of significant reduction in their characteristic flame spread, heat release, and smoke and toxic gas emissions E A K N82-29285# Federal Aviation Administration. Atlantic City. N J Fire Safety Branch THE DEVELOPMENT AND APPLICATIONS OF A FULL- SCALE WIDE BODY TEST ARTICLE TO STUDY THE BEHAVIOR OF INTERIOR MATERIALS DURING A POST- CRASH FUEL FIRE Constantme P Sarkos. Richard G Hill, and Wayne D Howell In AGARD Aircraft Fire Safety May 1982 21 p refs (For primary document see N82-29279 20-03) Avail NTIS HC A09/MF A01 The full scale, wide body test article was developed to study postcrash cabin .fires Applications of the C-133 article are described as follows (1) capabilities and instrumentation (2) derivation of fuel fire test conditions based on physical modeling and fire tests. (3) characterization of cabin fire hazards which result from exposure of wide body interior materials to external fuel fire, and (5) evaluation of effectiveness of urethane seat cushion fire blocking layers and improved cushioning materials It is shown that cabin hazards and parameters associated with postcrash fire can be realized by use of improved materi- als E A K N82-29286# British Aerospace Aircraft Group Bristol (England) Fire Precautions Engineering Dept AIRCRAFT POST CRASH FIRE REDUCTION/ SURVIVABIHTY ENHANCEMENT FROM A MANUFACTUR- ER'S VIEWPOINT T Madgwick In AGARD Aircraft Fire Safety May 1982 23 p refs (For primary document see N82-29279 20-03) Avail NTIS HC A09/MF A01 The importance of achieving a balanced level of overall safety for flight and crash situations are outlined Research and development in the area of external fire effects and occupant escape is evaluated The crashworthiness requirements developed for the SST and the means of compliance are outlined Cabin interior material combustion hazards are discussed Visibility tests in a smoke filled cabin and the relative importance of toxicity effects in hindering escape are assessed E A K N82-29287# Deutsche Forschungs- und Versuchsanstalt fuer Luft- und Raumfahrt Cologne (West Germany) Inst fuer Antnebstechmk AIRCRAFT POST-CRASH FIRE FIGHTING/RESCUE R Fiala In AGARD Aircraft Fire Safety May 1982 27 p refs (For primary document see N82-29279 20-03) Avail NTIS HC A09/MF A01 The correlation between specific extinguishing time and the size of the burning fuel area was calculated The influence of fuel properties the boiling temperature and viscosity on extinguishing efficiency of foams is described An extinguishing technique which considers the dependence of extinguishing efficiency on the foam properties is presented The requirements for foam monitors are shown The break up of foam |ets produced by foam monitors is discussed The extinguishing efficiency with the combined application of dry powder halon and foam and the advantages of a combined use when there is only a pool fire are outlined E A K N82-29288*# Princeton Umv N J Flight Research Lab DEVELOPMENT OF FLYING QUALITIES CRITERIA FOR SINGLE PILOT INSTRUMENT FLIGHT OPERATIONS Interim Report. Sep. 1979 - May 1981 Aharon Bar-Gill. W Barry Nixon and George E Miller Jun 1982 167 p refs (Contract NAS1-15764) (NASA-CR-165932. NAS 126165932 MAE-1528) Avail NTIS HC A08/MF A01 CSCL 17G Frying qualities criteria for Single Pilot Instrument Flight Rule (SPIFR) operations were investigated The ARA aircraft was modified and adapted for SPIFR operations Aircraft configurations to be flight-tested were chosen and matched on the ARA in-flight simulator, implementing modern control theory algorithms Mission planning and experimental matrix design were completed* Microprocessor software for the onboard data acquisition system was debugged and flight-tested Flight-path reconstruction nrocedure and the associated FORTRAN program were developed Algorithms associated with the statistical analysis of flight test results and the SPIFR flying qualities criteria deduction are discussed N W N82-29290# Federal Aviation Administration. Washington D C Office of Aviation Medicine EFFECTS OF APPROACH LIGHTING AND VARIATION IN VISIBLE RUNWAY LENGTH ON PERCEPTION OF AP- PROACH ANGLE IN SIMULATED NIGHT LANDINGS Henry W Mertens and Mark F Lewis Feb 1982 21 p refs (AD-A114742 FAA-AM-82-6) Avail NTIS HC A02/MF A01 CSCL 01/2 Previous experiments have demonstrated illusions due to variations in both length and width of runways in nighttime 'black hole approaches Even though approach lighting is not designed to provide vertical guidance, it is possible that cues from approach lights could interact with cues from runway lighting to reduce illusions due to variation in runway size Two experiments were conducted to evaluate the effect of approach lighting on perception of approach angle in simulated night approaches In the first experiment, 40 pilots made simulated visual approaches to a 150- by 6.000-ft runway with and without a 3.000-ft approach light system (ALSF-2) Pilots controlled a moving runway model to produce a constant 'normal' angle of approach over the distance range of 23,000 ft to 8,000 ft from threshold In the second experiment 24 pilots made simulated approaches to a 150- by 6.000-ft runway which was either fully visible or which had lights of the upwind half occluded In addition, a 1,400-ft abbreviated approach light system (SSALS) was used at three intensities Decreasing the visible length of the runway by occulting lights of the far half increased mean generated approach angles from 2 2 deg to 2 7 deg m agreement with results of a previous experiment involving similar lengths of runways Neither the presence of equal intensity approach lights nor uncomfortable glare from approach lights 20 times brighter than runway lights had an effect of practical significance on responses These findings reinforce previous experimental demonstrations of the importance of runway size cues related to varying runway length, and also show that potential size cues provided by approach lights do not prevent illusions due to variations in runway size GRA N82-29291# SRI International Corp Menlo Park. Calif TERMINAL INFORMATION DISPLAY SYSTEM BENEFITS AND COSTS Final Report Waheed Siddiqee, Janet Tornow, and Mma Chan Washington FAA Mar 1982 79 p refs (Contract DOT-FA-79-WA-4344) (AD-A114937. FAA-APO-82-4) Avail NTIS HC A05/MF A01 CSCL 17/7 533 N82-29292 Benefits and costs expected to accrue from a terminal information display system (TIDS) are analyzed TIOS is an electronic data processing system intended to replace (1) present flight data entry and printing equipment and (2) several devices currently used to display meteorological and operational informa- tion within towers and terminal radar control facilities A description of the terminal information display system is presented Major sources of both quantifiable and nonquantifiable benefits are discussed It is shown that the installation of TIOS would improve terminal controller productivity by ten to fifteen percent and would result in a substantial reduction in maintenance costs Information in present value (1981) dollars for the equipment life cycle is presented Over the twenty year service life of TIDS, the analysis indicates that the benefit/cost ratio is 1 74 and the net present value of savings by installing TIDS at thirty major terminal facilities is about $26 million GRA N82 29292# Applied Geophysics, Inc. Salt Lake City. Utah GEOPHYSICAL FLIGHT LINE FLYING AND FLIGHT PATH R E C O V E R Y UTILIZING THE LITTON LTN-76 INERTIAL NAVIGATION SYSTEM A F Mitkus. Dwight Cater. Patrick F Farmer, and S Parker Gay. Jr Nov 1981 177 p refs Prepared for High Life Helicopter. Inc (Contract DE-AC13-79GJ-01692) (DE82-005555. GJBX-363-81) Avail NTIS HC A09/MF A01 The Litton LTN-76 Inertial Navigation Systems (INS) with Inertial Track guidance system software is geared toward the airborne survey industry This report is a summary of tests performed with the LTN-76 designed to fly an airborne geophysical survey as well as to recover the subsequent flight path utilizing INS defived coordinates DOE N82-29293# Advisory Group for Aerospace Research and Development. Neuilly-Sur-Seme (France) HUMAN FACTORS IN AIR TRAFFIC CONTROL V David Hopkm (Royal Air Force Inst of Aviation Medicine) Apr 1982 187 p refs (AGARD-AG-275. ISBN-92-835-1421-1) Avail NTIS HC A09/MF A01 Human factors are related to air traffic control, air traffic control systems the physical surroundings, equipment, and operation of the system, and the selection, development, training and evaluation of air traffic controllers For individual titles, see N82-29294 through N82-29310 N82-29294# Advisory Group for Aerospace Research and Development Neuilly-Sur-Seme (France) THE AIR TRAFFIC CONTROL SYSTEM In its Human Factors in Air Traffic Control Apr 1982 p 3-9 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 Principles and practices of air traffic control are described The information influencing the air traffic control system and the information available to the controller are summarized and defined The users of air traffic control, whether commercial, military, or general aviation traffic is considered, are categorized, and their responsibilities discussed Interactions between air traffic control and the pilot are considered National and regional variations in the problems and practices of air traffic control are described j D N82-29295# Advisory Group for Aerospace Research and Development Neuilly-Sur-Seme (France) HUMAN FACTORS CONTRIBUTIONS TO AIR TRAFFIC CONTROL SYSTEMS In its Human Factors in Air Traffic Control Apr 1982 p 10-21 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 The role of the human factors specialist in air traffic control systems operations and planning is analyzed Man-machine interactions the contribution of human factors engineering to system design the implementation and testing of air traffic control systems and tasks, and the evolution of air traffic control systems and the educational role of human factors specialists as applied to air traffic control are considered J D N82-29296# Advisory Group for Aerospace Research and Development Neuilly-Sur-Seme (France) MAN AS A SYSTEM COMPONENT In its Human Factors in Air Traffic Control Apr 1982 p 22-30 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 The air traffic controller is considered as a component of a man-machine system Limitations of this approach are considered The allocation of functions the effects of automation and computer assistance, the man-machine interface and human reliability are discussed J D N82-29297# Advisory Group for Aerospace Research and Development, Neuilly-Sur-Seme (France) HUMAN CAPABILITIES AND LIMITATIONS IN SYSTEMS In its Human Factors in Air Traffic Control Apr 1982 p 31-46 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 Human capabilities and limitations which restrict the development of air traffic control systems are discussed Sensory factors, perception, learning, memory, capacity for attention, information processing, understanding, problem solving, decision making, and motivation are considered Common mismatches of system requirements with human capabilities are described J D N82-29298# Advisory Group for Aerospace Research and Development, Neuilly-Sur-Seme (France) JOBS AND TASKS IN AIR TRAFFIC CONTROL In its Human Factors in Air Traffic Control Apr 1982 p 47-52 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 Jobs and tasks are discussed The required content of job descriptions and their application to allocation of jobs is considered Task analysis and task synthesis, task grouping interactions between tasks, and workloads are described J D ' N82-29299^ Advisory Group for Aerospace Research and Development, Neuilly-Sur-Seme (France) THE WORK ENVIRONMENT In its Human Factors in Air Traffic Control Apr 1982 p 53-62 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 The work environment for all traffic control tasks is considered Principles of workspace design are discussed The physical environment, suites and consoles, air traffic control centers and control rooms, and air traffic control towers are described J D N82-29300# Advisory Group for Aerospace Research and Development. Neuilly-Sur-Seme (France) DISPLAYS In its Human Factors in Air Traffic Control Apr 1982 p 63-78 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 Factors affecting interactions between visual displays and their users are discussed The physical dimensions of the display, the layout of the display and of information within the display, the information content of the display, visual codings and color codings, the legibility and readability of displays, the relation between displays, and the quality of displayed information are considered New display technology is summarized J D N82-29301# Advisory Group for Aerospace Research and Development, Neuilly-Sur-Seme (France) CONTROLS In its Human Factors in Air Traffic Control Apr 1982 p 79-84 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 The location, type, sensitivity, and interactions of the controls used by the human to convey information to the air traffic control system are discussed The relationships between controls and visual displays are considered J D N82-29302# Advisory Group for Aerospace Research and Development. Neuilly-Sur-Seme (France) COMMUNICATIONS In its Human Factors in Air Traffic Control Apr 1982 p 85-93 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 The human factor terms of communication in air traffic control are examined The effects of known specified variables in communications on controller performance or system efficiency were measured The importance of speech and the use of computers in the man machine systems as a means of dialogue and information transmission is emphasized The following topics 534 N82-29317 are discussed transmission of information between air and ground, speech as a medium of communication qualitative attributes of speech, automated speech recognition and automated speech synthesis, coordination and liaison, language and terminology of air traffic control, air traffic phrasing and message formats, information quantification and redundancy in air traffic control messages E A K N82-293O9# Advisory Group for Aerospace Research and Development. Neuilly-Sur-Seme (France) ADDITIONAL FUNCTIONS WITHIN THE AIR TRAFFIC CONTROL SYSTEM In its Human Factors in Air Traffic Control Apr 1982 p 150-153 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 The application of human factors engineering to other job functions existing within the air traffic control system is discussed Personnel involved in data gathering, maintenance of system integrity, fault finding, supervision, and traffic control assistance are considered J D N82-29310# Advisory Group for Aerospace Research and Development, Neuilly-Sur-Seme (France) FUTURE TRENDS AND PROBLEMS In its Human Factors in Air Traffic Control Apr 1982 p 154-155 (For primary document see N82-29293 20-04) Avail NTIS HC A09/MF A01 Anticipated developments and problems occurring in the application of human factors engineering to air traffic control systems, particularly in the light of technological advances in hardware and software, are summarized J 0 N82-29311*# National Aeronautics and Space Administration Ames Research Center. Moffett Field. Calif ESTABLISHMENT OF A ROTOR MODEL BASIS R E McFarland Jun 1982 93 p-refs Prepared in cooperation with Army Aviation Research and Development Command. Moffett Field, Calif (NASA-TP-2026. A-8605. MAS 1 60 2026, AVRADCOM-TR-81-A-14) Avail NTIS HC A05/MF A01 CSCL 01C Radial-dimension computations in the RSRA's blade-element model are modified for both the acquisition of extensive baseline data and for real-time simulation use The baseline data, which are for the evaluation of model changes, use very small increments and are of high quality The modifications to the real-time simulation model are for accuracy improvement, especially when a minimal number of blade segments is required for real-time synchronization An accurate technique for handling tip loss in discrete blade models is developed The mathematical consistency and convergence properties of summation algorithms for blade forces and moments are examined and generalized integration coefficients are applied to equal-annuli midpoint spacing Rotor conditions identified as 'constrained' and balanced' are used and the propagation of error is analyzed Author N82-29312*# Cincinnati Univ. Ohio Dept of Aerospace Engineering and Applied Mechanics FLAP-LAG TORSIONAL DYNAMICS OF EXTENSIONAL AND INEXTENSIONAL ROTOR BLADES IN HOVER AND IN FORWARD FLIGHT Semiannual Progress Report, Jan -Jun. 1982 Crespo DaSilva Jun 1982 72 p refs (Grant NAG2-38) (NASA-CR-169159. NAS 126169159) Avail NTIS HC A04/MF A01 CSCL 01 C The reduction of the O(cu epsilon) mtegro differential equations to ordinary differential equations using a set of orthogonal functions is described Attention was focused on the hover flight condition The set of Galerkm integrals that appear in the reduced equations was evaluated by making use of nonrotatmg beam modes Although a large amount of computer time was needed to accomplish this task, the Galerkm integrals so evaluated were stored on tape on a permanent basis Several of the coefficients were also obtained in closed 'form in order to check the accuracy of the numerical computations The equilibrium solution to the set of 3n equations obtained was determined as the solution to a minimization problem S L N82-29313*# National Aeronautics and Space Administration Langley Research Center. Hampton. Va THE FEASIBILITY OF A HIGH-ALTITUDE AIRCRAFT PLATFORM WITH CONSIDERATION OF TECHNOLOGICAL AND SOCIETAL CONSTRAINTS Thesis - Kansas Univ Ernald B Graves Jun 1982 250 p refs (NASA-TM-84508 NAS 11584508) Avail NTIS HC A15/MF A01 CSCL 01C The feasibility of remotely piloted aircraft performing year around missions at an altitude of 70 000 feet is determined Blimp and airplane type vehicles employing solar-voltaic, microwave, or nuclear propulsion systems were considered A payload weighing 100 pounds and requiring 1000 watts of continuous power was assumed for analysis purposes Results indicate that a solar powered aircraft requires more solar cell area than is available on conventional aircraft configurations if designed for the short days and high wind speeds associated with the winter season A conventionally shaped blimp that uses solar power appears feasible if maximum airspeed is limited to about 100 ft/s No viable airplane configuration that uses solar power and designed to withstand the winter environment was found Both a conventionally shaped blimp and airplane appear feasible using microwave power Nuclear powered aircraft of these type are also feasible Societal attitudes toward the use of solar power in high altitude aircraft appear favorable The use of microwave power for this purpose is controversial, even though the ground station required would transmit power at levels comparable to existing satellite communications stations S L N82-29315*# Bell Helicopter Co. Fort Worth, Tex INVESTIGATION OF CORRELATION BETWEEN FULL- SCALE AND FIFTH-SCALE WIND TUNNEL TESTS OF A BELL HELICOPTER TEXTRON MODEL 222 Final Report Patrick K Squires Jun 1982 401 p refs (Contract NAS2-10773) (NASA-CR-166362. NAS 1 26 166362) Avail NTIS HC A18/MF A01 CSCL01C Reasons for lack of correlation between data from a fifth-scale wind tunnel test of the Bell Helicopter Textron Model 222 and a full-scale test of the model 222 prototype in the NASA Ames 40-by 80-foot tunnel were investigated This investigation centered around a carefully designed fifth-scale wind tunnel test of an accurately contoured model of the Model 222 prototype mounted on a replica of the full-scale mounting system The improvement in correlation for drag characteristics in pitch and yaw with the fifth-scale model mounted on the replica system is shown Interference between the model and mounting system was identified as a significant effect and was concluded to be a primary cause of the lack of correlation in the earlier tests Author N82-29316*# Massachusetts Inst of Tech , Cambridge Flight Transportation Lab THE COST OF NOISE REDUCTION FOR DEPARTURE AND ARRIVAL OPERATIONS OF COMMERCIAL TILT ROTOR AIRCRAFT Henry B Faulkner and William M Swan Jun 1976 118 p refs (Contract NAS2-7620) (NASA-CR-137803 NAS 126137803) Avail NTIS HC A06/MF A01 CSCL01C The relationship between direct operating cost (DOC) and noise annoyance due to a departure and an arrival operation was developed for commercial tilt rotor aircraft This was accomplished by generating a series of tilt rotor aircraft designs to meet various noise goals at minimum DOC These vehicles ranged across the spectrum of possible noise levels from completely unconstrained to the quietest vehicles that could be designed within the study ground rules Optimization parameters were varied to find the minimum DOC This basic variation was then extended to different aircraft sizes and technology time frames Author N82-29317*# National Aeronautics and Space Administration Langley Research Center. Hampton. Va AUTOMATED OPTIMUM DESIGN OF WING STRUCTURES DETERMINISTIC AND PROBABILISTIC APPROACHES S S Rao Aug 1982 47 p refs (NASA-TM-84475, L-15169. NAS 11584475) Avail NTIS HC A03/MF A01 CSCL01C The automated optimum design of airplane wing structures subjected to multiple behavior constraints is described The structural mass of the wing is considered the objective function 535 N82-29318 The maximum sttess, wing tip deflection, root angle of attack, and flutter velocity during the pull up maneuver (static load), the natural frequencies of the wing structure and the stresses induced in the wing structure due to landing and gust loads are suitably constrained Both deterministic and probabilistic ap- proaches are used for finding the stresses induced in the airplane wing structure due to landing and gust loads A wing design is represented by a uniform beam with a cross section in the form of a hollow symmetric double wedge The airfoil thickness and chord length are the design variables, and a graphical procedure is used to find the optimum solutions A supersonic wing design is represented by finite elements The thicknesses of the skin and the web and the cross sectional areas of the flanges are the design variables, and nonlinear programming techniques are used to find the optimum solution S L N82-29318# Aeronautical Research Labs, Melbourne (Australia) A DISCUSSION OF THE FLYING QUALITY REQUIREMENTS OF_A_ BASIC TRAINING AIRCRAFT C A Martin Mar 1982 16 p refs (AD-A114805, ARL/AERO-TM-337) Avail NTIS HC A02/MF A01 CSCL 01/3 This Memo aims to identify flying qualities of importance in a basic training aircraft and also to suggest interpretations of particular military specifications The proposition is developed that flying qualities which are considered good for an operational aircraft are not necessarily desirable for a training aircraft GRA N82-29319*# National Aeronautics and Space Administration Langley Research Center Hampton, Va HEADS UP DISPLAY Patent Application H Douglas Garner and William E Howell. inventors (to NASA) Filed 28 May 1982 12 p (NASA-Case-LAR-12630-1 US-Patent-Appl-SN-383384| Avail NTIS HC A02/MF A01 CSCL 01D A heads up aircraft display which allows the pilot to view the display without diverting his attention from the scene ahead is disclosed The display is designed for use on propeller driven aircraft comprised of a radially disposed row of lamps embedded in the rear surface of a propeller Measurements of flight data are made by conventional means and converted into digital signals These digital signals are applied to graphic generators which control lamp drivers which in turn control lamps through slip rings The lamps are lit at the appropriate times during each revolution of the propeller to display the flight data in graphic form to the pilot The combination of graphic generators and radially disposed lamps embedded in an aircraft propeller enables the pilot to view the display without diverting his attention from the scene ahead NASA action to be carried out more effectively The trial was conducted on Hercules aircraft, and the initial analysis of results was carried out by personnel who are responsible for maintenance of these aircrafts Operating instructions for aircrew and maintenance personnel and the results of the trial are presented Details of the rationale behind the monitoring procedures and overall conclusions on the trial are given S L N82-29323*# Teledyne CAE. Toledo, Ohio COOLED VARIABLE NOZZLE RADIAL TURBINE FOR ROTOR CRAFT APPLICATIONS C Rogo Mar 1981 205 p refs (Contract NAS3-22005. DA Proj 1 L1-62209-AH-76) (NASA-CR-165397 NAS 126165397 Rept-1759) Avail NTIS HC A10/MF A01 CSCL21E An advanced, small 2 27 kb/sec (5 Ibs/sec), high temperature, variable area radial turbine was studied for a rotor craft application Variable capacity cycles including single-shaft and free-turbine engine configurations were analyzed to define an optimum engine design configuration Parametric optimizations were made on cooled and uncooled rotor configurations A detailed structural and heat transfer analysis was conducted to provide a 4000-hour life HP turbine with material properties of the 1988 time frame A pivoted vane and a moveable sidewall geometry were analyzed Cooling and variable geometry penalties were included in the cycle analysis A variable geometry free-turbine engine configura- tion with a design 1477 K (2200 F) inlet temperature and a compressor pressure ratio of 16 1 was selected An uncooled HP radial turbine rotor with a moveable sidewall nozzle showed the highest performance potential for a time weighted duty cycle Author N82-29324*# National Aeronautics and Space Administration Lewis Research Center. Cleveland, Ohio QCSEE OVER THE WING ENGINE ACOUSTIC DATA Harry E Bloomer and Irvm J Loeffler May 1982 28 p refs (NASA-TM-82708 E-990 NAS 1 15 82708) Avail NTIS HC A03/MF A01 CSCL 21E The over the wing (OTW) Quiet, Clean, Short Haul Experimen- tal Engine (QCSEE) was tested at the NASA Lewis Engine Noise Test Facility A boilerplate (nonflight weight), high throat Mach number acoustically treated inlet and a D shaped OTW exhaust nozzle with variable position side doors were used in the tests along with wing and flap segments to simulate an installation on a short haul transport aircraft All of the acoustic test data from 10 configurations are documented in tabular form Some selected narrowband and 1/3 octave band plots of sound pressure level are presented Author N82-29321# National Center for Atmospheric Research, Boulder, Colo Atmospheric Technology Div AN EVALUATION OF THE ROSEMOUNT ICE DETECTOR FOR CLOUD WATER CONTENT MEASUREMENTS E N Brown Oct 1981 19 p refs (Grant NSF ATM-77-23757) (PB82-158833, NCAR/TN-183) Avail NTIS HC A02/MF A01 CSCL 14B A Rosemount ice detector was installed on a Research Aviation Facility Queen Air for evaluation It was used during a winter stratus cloud experiment at Muskegon Michigan (1978) and also during a cumulus cloud experiment (HIPLEX) in 1980 at Big Spring. Texas Results indicate that the detector is an extremely sensitive instrument with a reasonable dynamic range The instrument provides a measurement of icing severity and valid computed water content values only for conditions of small water content and/or low temperature GRA N82-29322# Aeronautical Research Labs , Melbourne (Australia) RESULTS OF T56 ENGINE PERFORMANCE MONITORING TRIAL IN HERCULES AIRCRAFT, FEBRUARY - JULY 1977 D E Glenny Apr 1981 37 p refs (ARL-MECH-Eng-TECH-MEMO-409 AR-002-277) Avail NTIS HC A03/MF A01 An engine performance monitoring trial was carried out on the Hercules aircraft The engine monitoring procedures were developed as an aid to the flight engineer and the maintenance section so that the performance of the Allison T56 engines were monitored more closely than was specified in operating procedures, thus enabling engine operation and maintenance N82-29325# Exotech Proprietary Ltd . Monterey, Calif MULTISTAGE AXIAL COMPRESSOR PROGRAM ON TIP CLEARANCE EFFECTS Contractor Report. May 1979 - Aug. 1981 I Moyle Aug 1981 49 p refs (Contract N62271-80-M-2504) (AD-A107445, NPS67-81-01CR) Avail NTIS HC A03/MF A01 CSCL 21/5 Tip clearance has long been known to be a source of losses in axial compressors with cantilevered blades The reasons for the losses, however, are not well understood and current practice in engine design still requires extensive effort to maintain constant minimal operating clearances over a wide range of conditions The emphasis on clearance control may be appreciated by the typical observation that a ten percent change in peak static pressure rise in a compressor stage may occur for a fifty percent change in clearance Clearances are typically in the one to five percent of major passage dimension range, and thus a small change in passage dimensions represents a large change in clearance It is clear that, in general, it would be desirable that blading performance be less sensitive to changes in clearance Less sensitivity would allow a general relaxation of the mechani- cal tolerances on a compressor assembly and provide more consistent transient performance The aerodynamics of achieving such a situation are a challenge as the underlying requirement is improved performance at larger clearances Work toward understanding the basic mechanisms of tip clearance effects with an emphasis on designing for clearance has been commenced at the Naval Postgraduate School Turbopropulsion Laboratory (NPS/TPL) This report summarizes the preliminary work on the Multistage Compressor (MSC) facility at the Laboratory GRA 536 N82-29332 N82-29326jjl Purdue Univ . Lafayette. Ind School of Mechanical Engineering WATER INGESTION INTO AXIAL FLOW COMPRESSORS. PART 3: EXPERIMENTAL RESULTS AND DISCUSSION Final Report. 15 Dec. 1977 - 30 Jun. 1981 T Tsuchiya. S N B Murthy. C M Ehresman. and D Richards Wright-Patterson AFB Ohio AFWAL Oct 1981 268 p refs (Contract F33615-78-C-2401. AF Proj 3066) (AD-A114830. AFWAL-TR-80-2090-PI-3) Avail NTIS HC A13/MF A01 CSCL 21/5 The subject of air-water mixture flow in axial compressors of jet engines is of practical interest in two contexts of water ingestion during take-off from rough runways with puddles of water and during flight through rain storms The change in the compressor performance in turn produces changes in the performance of other components and of the engine as a whole During the current investigation. (1) an analysis of the effects of water ingestion into a compressor has been carried out leading to the development of a predictive code, the PURDU-WICSTK program and (2) a series of tests have been carried out on a small test compressor with mixtures of gases (containing methane gas to simulate steam) and with air-water droplet mixtures The experimental results have been compared with predictions It is concluded that the basic effects of water ingestion into compressors arise through (1) blockage. (2) distor- tion and (3) heat and mass transfer processes, the changes in blade aerodynamic performance being relatively small In the case of a compressor of small mass flow and pressure ratio and high operating speed, increased quantities of water ingestion give rise to large quantities of water in the tip region GRA N82-29327jjl Purdue Univ . Lafayette. Ind School of Mechanical Engineering EFFECT OF WATER ON AXIAL FLOW COMPRESSORS. PART 2: COMPUTATIONAL PROGRAM Final Report. 16 Dec. 1977 - 30 Sep. 1980 T Tsuchiya and S N B Murthy Wright-Patterson AFB. Ohio AFWAL Jun 1981 425 p refs (Contract F33615-78-C-2401. AF Proj 3066) (AD-A114831. AFWAL-TR-80-2090-PI-2) Avail NTIS HC A18/MF A01 CSCL 21/5 An analysis of the performance of an axial flow compressor operating with mixtures of gases and air-water droplet mixtures was performed In the case of mixtures of gases, account was taken of the changes in molecular weight and ratio of specific heats In the case of two phase flow, the major processes of interest are (1) droplet blade interaction. (2) droplet heating. (3) droplet centrifugmg. and (4) droplet break up The PURDU- WICSTK program developed for the prediction of compressor performance was utilized to obtain the performance of a test compressor A three dimensional stream line computer code the UD-0300, was also modified and exercised in the case of compressor operation with mixtures of gases Water ingestion into the compressor of an aircraft gas turbine engine affects the performance of the engine, and a preliminary analysis of the nature of the effects was also conducted M G N82-29328# Iowa State Univ of Science and Technology. Ames Turbomachmery Components Research Lab AERODYNAMICS OF ADVANCED AXIAL-FLOW TURBO- MACHINERY Annual Report. 1 Oct. 1980 - 30 Sep. 1981 George K Serovy. Patrick Kavanagh. and Theodore H Oknshi Dec 1981 82 p refs (Grant AF-AFOSR-0004-80. AF Proj 2307) (AD-A114911 ISU-ERI-AMES-82108 TCRL-22. AFOSR-82-0201TR) Avail NTIS HC A05/MF A01 CSCL 21/5 A multi-task research program on the aerodynamics of advanced axial-flow turbomachmery is continuing at Iowa State University Program components are intended to result in direct contributions to the improvement of axial-flow fan. compressor, and turbine design procedures A detailed experimental investiga- tion of mtrapassage flow in a large-scale, curved, rectangular cross section channel representative of turbomachmery passages is in progress Author (GRA) N82-29329*# National Aeronautics and Space Administration llangley Research Center. Hampton. Va AGRICULTURAL AIRPLANE MISSION TIME STRUCTURE CHARACTERISTICS Joseph W Jewel. Jr Jul 1982 44 p refs (NASA-TM-84470. L-15125. NAS 11584470) Avail NTIS HC A03/MF A01 CSCL 01C The time structure characteristics of agricultural airplane missions were studied by using records from NASA VGH flight recorders Flight times varied from less than 3 minutes to more than 103 minutes There was a significant reduction in turning time between spreading runs as pilot experience in the airplane type increased Spreading runs accounted for only 25 to 29 percent of the flight time of an agricultural airplane Lowering the longitudinal stick force appeared to reduce both the turning time between spreading runs and pilot fatigue at the end of a working day Author N82-29330* National Aeronautics and Space Administration John F Kennedy Space Center, Cocoa Beach. Fla METHOD FOR REFURBISHING AND PROCESSING PARACHUTES Patent Russell T Crowell. inventor (to NASA) Issued 2 Feb 1982 7 p Filed 30 May 1980 Supersedes N81-14967 (19 - 06. p 0706) Division of US Patent Appl SN-862878, filed 12 Dec 1977. US Patent-4.244.810 (NASA-Case-KSC-11042-1. US-Patent-4.313.291. US-Patent-4.244 810 US-Patent-Appl-SN-154663 US-Patent-Appl-SN-862878 US-Patent-Class-53-429. US-Patent-Class-8-150) Avail US Patent and Trademark Office CSCL 14B A system and method for refurbishing and processing parachutes is discussed including an overhead monorail conveyor system on which the parachute is suspended for horizontal conveyance The parachute is first suspended in partially open tented configuration wherein open inspection of the canopy is permitted to remove debris and inspect all areas Following inspection, the parachute is transported by the monorail conveyor to a washing and drying station with the parachute canopy mounted on the conveyor ina systematic arrangement which permits water and air to pass through the nbbonhke material of the canopy Following drying of the parachute the parachute is conveyed into an interior space where it is finally inspected and removed from the monorail conveyor and laid upon a table for folding Official Gazette of the U S Patent and Trademark Office N82-29331*# National Aeronautics and Space Administration John F Kennedy Space Center Cocoa Beach. Fla INFLIGHT IFR PROCEDURES SIMULATOR Patent Apphca-, tion Lloyd C Parker inventor (to NASA) Filed 11 Jun 1982 22 p (NASA-Case-KSC-11218-1 US-Patent-Appl-SN-387649) Avail NTIS HC A02/MF A01 CSCL 14B An m-fhght trainer designed to tram students in a conven- tional aircraft is disclosed The trainer generates simulated signals and commands to conventional instruments provided in the aircraft that correspond to the normal signals a pilot receives during instrument flight rule (IFR) flights and landing and departure procedures Results of studies conducted using apparatus which demonstrated the concept indicate that the concept is feasible Also students trained using only the In-flight IFR Simulator were more proficient in skills development than those trained using table-top simulators and in aircraft in the conventional manner J M S N82-29332# Seville Research Corp Pensacola Fla OPERATIONAL TEST AND EVALUATION HANDBOOK FOR AIRCRAFT TRAINING DEVICES VOLUME 1 PLANNING AND MANAGEMENT Final Report Thomas H Gray. Stephen R Osborne Roik I Hockenberger and James P Smith Williams AFB Ariz An Force Human Resources Lab Feb 1982 72 p refs (Contract F33615-78-C-0063 AF Proi 1123) (AD-A112498 AFHRL-TR-81-44-Vol-1) Avail NTIS HC A04/MF A01 CSCL 05/9 The handbook comprised of three volumes is intended to provide guidelines and procedures appropriate for An Force Operational Test and Evaluation (OT/E) personnel to use in planning conducting and reporting the results of simulator assessment efforts Although of value of all test personnel it is primarily for the typical novice test manager/director-a person who has subject matter expertise (e g a qualified pilot or operator) but who may have little or no previous OT/E experience The handbook provides detailed coverage on OT/E planning and management with special emphasis on measuring device operational effectiveness and suitability In accord with its objectives the handbook was prepared 10 serve as a supplemeni to Air Force Manual 55 43 Management of Operational Tesl 537 N82-29333 and Evaluation', by providing those specific additional evaluation concepts and techniques necessary for aircrew training device (ATD) test and evaluation Volume 1 is concerned first with describing both general and specific ATD OT/E planning and management considerations and links those events which occur early in the ATD acquisition process to later ATD OT/E planning and management activities It defines the various evaluation concepts germane to understanding ATD OT/E. and describes the two major ATD OT/E activmes--lnitial/Qualificatton OT/E and Follow-on OT/E matters of ATD value and worth to the Air Force The acquisition and life cycle costs associated with modern ATDs make such concerns important GRA N82-29333# Calspan Field Services Inc. Arnold Air Force Station. Tenn THE USE OF A MULTI DEGREE OF FREEDOM DUAL BALANCE SYSTEM TO MEASURE CROSS AND CROSS- COUPLING DERIVATIVES Final* Report. 1 Oct. - 1 Nov. 1981 D R Haberman AEOC Apr 1982 92 p refs Sponsored by Air Force (AD-A114813. AEDC-TR-81-34) Avail NTIS HC A05/MF A01 CSCL 12/1 The equations of motion are derived for two existing dual balance systems used at the Arnold Engineering Development Center (AEDC) to obtain measurements of aerodynamic cross and cross-coupling derivatives The complete equations of motion presented include the effects of sting motion Each system incorporates a dynamic cross flexure balance and a five-component static balance The primary deflection modes of the balances were confirmed using a holographic interferometry measurement technique Both laboratory and wind tunnel data are presented to illustrate dynamic effects Author (GRA) N82-29334# Advisory Group for Aerospace Research and Development Neuilly-Sur-Seme (France) Fluid Dynamics Panel WINDTUNNEL CAPABILITY RELATED TO TEST SECTIONS. CRYOGENICS, AND COMPUTER WINDTUNNEL INTEGRA- TION Apr 1982 64 p refs (AGARD-AR-174, ISBN-92-835-1420-3) Avail NTIS HC A04/MF A01 The roles of computational fluid dynamics and wind tunnels, and their growing interdependence are considered Transonic test sections, cryogenic testing technology, and integration of computer and wind tunnel testing are discussed S L N02-29343# Sandia Labs . Albuquerque. N Mex Aerodynamic Simulation Div USER'S MANUAL FOR THE AMEER FLIGHT PATH- TRAJECTORY SIMULATION CODE Eugene J Meyer Oct 1981 187 p refs (Contract DEOAC04-76DP-00789) (DE82-007004 SAND-80-2056) Avail NTIS HC A09/MF A01 A guide to the use of the AMEER (Aero-Mechanical Equations Evaluation Routines) flight path-trajectory simulation code is presented The input data requirements, computed output data available, code control features, and code flow logic are described for a rigid-body six-degree-of-freedom or point mass simulation DOE N82-29347# Institute de Pesquisas Espaciais. Sao Jose dos Campos (Brazil) PRELAUNCH ESTIMATES OF NEAR EARTH SATELLITE LIFETIMES USING QUASI-DYNAMIC ATMOSPHERE MODELS - APPLICATION TO A PROPOSED BRAZILIAN SATELLITE Nellore S Venkataraman and Kondapalli Rama Rao Feb 1982 22 p refs Submitted for publication (INPE-2325-PRE/080) Avail NTIS HC A02/MF A01 A rapid prelaunch estimate of near Earth satellite lifetimes using the small perturbation theory is calculated A quasi-dynamic atmospheric model is used employing a different exospheric temperature every three months The drag coefficient is calculated using kinetic theory S L N82-29393# Ellis (George S). Chardon. Ohio ETHANOL PRODUCTION BY VAPOR COMPRESSION DISTILLATION Final Report George S Ellis 1981 9 p (Contract DE-FG02-80R5-10240) (DE82-004892. DOE/R5-10240/2) Avail NTIS HC A02/MF A01 It was the goal of the project to develop and demonstrate a one (1) gallon per hour vapor compression distillation unit for fuel ethanol production that could be profitably manufactured and economically operated by individual family units The unit constructed was originally built for strictly ambient temperature operation, but later modified to permit elevated temperature operation It successfully separated ethanol from a dilute solution, but only at a very low production rate The initial configuration had the compressor located outside of the distillation vessel and was losing excessive energy to the environment Therefore, it would not be possible to operate that design at elevated temperature Thus, the compressor was moved inside the distillation vessel DOE N82-29464# Brookhaven National Lab Upton. N Y WATER-COMPATIBLE POLYMER CONCRETE MATERIALS FOR USE IN RAPID REPAIR SYSTEMS FOR AIRPORT RUNWAYS Final Report. Mar. 1980 - Feb. 1981 T Sugama and L E Kukacka Mar 1981 128 p refs (Contracts AFOSR ISSA 80-00027. DE-AC02-76CH-00016. AF Proj 2307) (DE82-010994. BNL-51390. AFOSR-81-0589TR) Avail NTIS HC A07/MF A01 Water-compatible polymer concrete (PC) formulations were developed which appear to have potential for use in all-weather rapid repair procedures for bomb-damaged runways Formulations consisting of furfuryl alcohol, water-saturated aggregate, dry silica flour, promoters, and catalysts produced composites with properties suitable for repair purposes when mixed and polymer- ized at temperatures from -200 to 300 C Calcium-unsaturated polyester complexed PC also produced excellent properties However, the early strength criteria [2000 psi (1378 MPa) at 1 h] and other requirements such as compatibility of the formulation with water and practical working times could be attained only at temperatures > 200 C This system can be polymerized under water Studies of the polymerization reaction mechanisms, materials properties, costs, and potential placement methods were performed DOE N82 29476# UOP Inc . Des Plames. Ill UNITED STATES AIR FORCE SHALE OIL TO FUELS. PHASE 2 Interim Technical Report. 1 Apr. 1979 - 30 Sep. 1980 J R Wilcox. J G Sikonia. T G Board, and F J Riedl Wright-Patterson AFB, Ohio AFWAL Nov 1981 295 p refs (Contract F33615-78-C-2079) (AD-A114531. AFWAL-TR-81-2116) Avail NTIS HC A13/MF A01 CSCL 21/4 Phase II of this project was conducted to demonstrate innovative technology to reduce the cost of converting shale oil to high yields of aviation turbine fuels To carry out this program. UOP selected a processing scheme involving hydrocrackmg as the primary conversion unit The Phase II program included pilot plant processing, fouling studies and economic analysis The pilot plant operations performed during Phase II involved four specific processing steps feed preparation, low pressure hydrotreating. high pressure hydrotreating, and hydrocrackmg Two shale oil feedstocks were utilized for each processing step shale oil derived from Occidental Modified In-Situ retort and shale oil obtained from the Paraho direct-heated retort Using data generated from the pilot plant operations and the study basis provided by the USAF. economic analyses were performed to find the cost of production of jet fuel, and total liquid product at a 15% discounted cash flow rate of return (DCFRR) on investment GRA N82-29510*# Draper (Charles Stark) Lab. Inc. Cambridge. Mass SYSTEM DATA COMMUNICATION STRUCTURES FOR ACTIVE-CONTROL TRANSPORT AIRCRAFT. VOLUME 1 Final Report A L Hopkins. J H Martin. L D Brock. D G Jansson. S Serben. T B Smith, and L D Hanley Jun 1981 236 p refs 2 Vol (Contract NAS1-15359) (NASA-CR-165773-Vol-1. NAS 1 26 165773-Vol-1. R-1469-Vol-1) Avail NTIS HCA11/MFA01 CSCL 178 538 N82-29800 Candidate data communication techniques are identified, including dedicated links, local buses, broadcast buses, multiplex buses, and mesh networks The design methodology for mesh networks is then discussed, including network topology and node architecture Several concepts of power distribution are reviewed, including current limiting and mesh networks for power The technology issues of packaging, transmission media, and lightning are addressed, and, finally, the analysis tools developed to aid in the communication design process are described There are special tools to analyze the reliability and connectivity of networks and more general reliability analysis tools for all types of systems S L N82-29511'# Draper (Charles Stark) Lab. Inc'. Cambridge. Mass SYSTEM DATA COMMUNICATION STRUCTURES FOR ACTIVE-CONTROL TRANSPORT AIRCRAFT. VOLUME 2 Final Report A L Hopkins. J H Martin, L D Brock, D G Jansson, S Serben, T B Smith, and L D Hanley Jun 1981 156 p refs 2 Vol (Contract NAS1-15359) (NASA-CR-165773-Vol-2. NAS 1 26 165773-Vol-2. R-1469-Vol-2) Avail NTIS HC A08/MF A01 CSCL 17B The application of communication structures to advanced transport aircraft are addressed First, a set of avionic functional requirements is established, and a baseline set of avionics equipment is defined that will meet the requirements Three alternative configurations for this equipment are the.n identified that represent the evolution toward more dispersed systems Candidate communication structures are proposed for each system configuration, and these are compared using trade off analyses, these analyses emphasize reliability but also address complexity Multiplex buses are recognized as the likely near term choice with mesh networks being desirable for advanced, highly dispersed systems S L N82-29520# Lincoln Lab. Mass Inst of Tech . Lexington MOVING TARGET DETECTOR (MOD 2) David Karp and John R Anderson 3 Nov 1981 159 p refs (Contracts DOT-FATQ-WAI-679. F19628-80-C-0002) (AD-A114709, ATC-95, FAA-RD-80-77) Avail NTIS HC A08/MF A01 CSCL 17/9 Under FAA sponsorship, MIT/Lincoln Laboratory has developed a second generation, field operable Moving Target Detection System (MTD-II) which has been tested at operational FAA terminal and enroute radar sites, and serves as the basis for the ASR-9 MTD technical performance specifications This summary report covers the period October, 1976 through September, 1979 in which design, development, field testing and system performance evaluation were carried out Report No FAA-RD-76-190. ATC-69. 'Description and Performance Evaluation of the Moving Target Detector' dated 8 March 1977. serves as the technical foundation of this work MTD-processmg design modifications were effected to handle conditions of excessive ground clutter and moving ground traffic The rationale for the modified algorithms is provided, and measured perfor- mance characteristics at several FAA field sites are discussed Author (GRA) N82-29527# Advisory Group for Aerospace Research and Development. Neuilly-Sur-Seme (France) ELECTROMAGNETIC PROPAGATION PROBLEMS IN THE TACTICAL ENVIRONMENT Apr 1982 155 p refs Lecture Series held in Munich. 3-4 May 1982 and Paris, 6-7 May 1982 (AGARD-LS-120. ISBN-92-835-1419-X) Avail NTIS HC A08/MF A01 Propagation criteria affecting the performance of electronic equipment under battlefield conditions are discussed For individual titles, see N82-29528 through N82-29537 N82-29535# Royal Aircraft Establishment. Farnborough (England) PROPAGATION PROBLEMS ASSOCIATED WITH AIR- CRAFT COMMUNICATIONS SYSTEMS B Burgess In AGARD Electromagnetic Propagation Probl in the Tactical Environ Apr 1982 10 p refs (For primary document see N82-29527 20-32) Avail NTIS HC A08/MF A01 Communications with mobiles is assuming increasing importance in a military context, with the advances in technology enabling not only greater amounts of information to be transferred, but also fostering a much harsher electromagnetic environment The trend towards digital communications systems coupled with the possible demand for the wider bandwidths means that the propagation medium characteristics that influence the performance of these links are somewhat different from those that need to be addressed for narrowband analogue modulation transmissions The various types of communications systems that are used with aeromobile platforms are reviewed and the various propagation problems that arise in achieving systems with good overall performance discussed The links are conveniently divided into two types beyond line of sight and line of sight systems, and span the frequency range from LF through to microwaves Author N82-29555# Syracuse Univ N Y Dept of Physics COMPUTER ENHANCED ANALYSIS OF A JET IN A CROSS-STREAM John W Trischka and Nancy J Birkenheuer (Midwest Research Inst. Golden, Colo ) 22 Feb 1982 41 p refs Backup document for AIAA synoptic scheduled for publication in the AIAA Journal, Feb 1983 Avail NTIS HC A03/MF A01 Previously analyzed velocity data for a jet in a wind tunnel cross stream was used in a computer analysis which, through interpolation and extrapolation, produced velocity and vorticity fields on a uniform three dimensional grid Microfilm output from the computer displayed isopleths on sets of planes in three orthogonal directions Improved determinations were made of the |et center line of the center lines of the bound vortices and of the get boundaries Stationary waves were discovered in the mixing region on the upstream side of the jet An explanation for these waves is proposed The angle between vorticity and velocity is used to compare the flow with complex lamellar and Beltrami flows A convergence feature in the jet wake is noted Author N82-29556*# National Aeronautics and Space Administration Ames Research Center. Moffett Field, Calif CORRELATION OF PRESTON-TUBE DATA WITH LAMINAR SKIN FRICTION (LOG NO. J12984) T D Reed (Oklahoma State Univ, Stillwater), A Abu-Mostafa (Oklahoma State Univ , Stillwater), and F W Stemle, Jr 18 Jan 1982 37 p refs Backup document for AIAA Synoptic scheduled for publication in AIAA Journal in Feb 1983 (Grants NSG-2396, NAG2-76) (NASA-TM-84827 NAS 11584827, Log-J12984) Avail NTIS HC A03/MF A01 CSCL 200 Preston tube data within laminar boundary layers obtained on a sharp ten-degree cone in the NASA Ames eleven-foot transonic wind tunnel are correlated with the corresponding values of theoretical skin friction Data were obtained over a Mach number range of 0 30 to 0 95 and unit Reynolds numbers of 984, 131, and 164 million per meter The rms scatter of skin friction coefficient about the correlation is of the order of one percent, which is comparable to the reported accuracy for calibrations of Preston tubes in incompressible pipe flows In contrast to previous works on Preston tube/skin friction correlations, which are based on the physical height of the probe's face, this satisfactory correlation for compressible boundary layer flows is achieved by accounting for the effects of a variable "effective height of the probe The coefficients, which appear in the correlation, are dependent on the particular tunnel environ- ment The general procedure can be used to define correlations for other wind tunnels Author N82-29800# Electro Magnetic Applications. Inc , Denver. Colo ATMOSPHERIC ELECTRICITY HAZARDS ANALYTICAL MODEL DEVELOPMENT AND APPLICATION. VOLUME 1. LIGHTNING ENVIRONMENT MODELING Final Report. Aug. 1979 - Jun. 1982 Martin A Uman (Lightning Location and Protection Inc) and E Philip Krider (Lightning Location and Protection, Inc ) Wright- Patterson AFB, Ohio AFWAL Aug 7981 172 p refs 3 Vol (Contract F33615-79-C-3412. AF Proj 2402) (AD-A114015. EMA-81-R-21-Vol-1. AFWAL-TR-81-3084-VOI-1) Avail NTIS HC A08/MF A01 CSCL 04/1 The state of the art of lightning phenomenology and its 539 N82-29801 electromagnetic environment is reviewed All aspects and phases are discussed A model is chosen for each phase which best describes what is currently known and understood Computer models for predicting the electromagnetic environment for several of the processes are given, along with numerical predictions A comprehensive bibliography is also provided Author N82-29801# Lightning and Transients Research Inst. Melbourne Fla ATMOSPHERIC ELECTRICITY HAZARDS ANALYTICAL MODEL DEVELOPMENT AND APPLICATION. VOLUME 2: SIMULATION OF THE LIGHTNING/AIRCRAFT INTERAC- TION EVENT Final Report, Aug. 1979 - Jun. 1981 John D Robb Wright-Patterson AFB, Ohio AFWAL Jun 1981 59 p refs 3 Vol (Contract F33615-79-C-3412. AF Proj 2402) (AD-A114016. EMA-81-R-21-Vol-2. AFWAL-TR-81-3084-Vol-2) Avail NTIS HC A04/MF A01 CSCL 04/ 1 A review of currently used lightning test techniques for aircraft is given The requirements for lightning simulation are given and discussed Finally, a new approch for simulating the lightning/aircraft interaction is presented, and is based on nuclear electromagnetic pulse (NEMP) technology GRA N82-29802# Electro Magnetic Applications. Inc , Denver. Colo ATMOSPHERIC ELECTRICITY HAZARDS ANALYTICAL MODEL DEVELOPMENT AND APPLICATION. VOLUME 3: ELECTROMAGNETIC COUPLING MODELING OF THE LIGHTNING/AIRCRAFT INTERACTION EVENT Final Report. Aug. 1979 - Jun 1981 F J Enksen, T H Rudolph, and Rodney Perala Wright-Patterson A'FB. Ohio AFWAL Jun 1981 330 p refs 3 Vol (Contract F33615-79-C-3412, AF Proj 2402) (AD-A114017, EMA-81-R-21-Vol-3, AFWAL-TR-81-3084-Vol-3) Avail NTIS HC A15/MF A01 CSCL 04/1 The state of the art of coupling of electromagnetic fields to aircraft is reviewed Assessing the electromagnetic interaction of lightning with aircraft is considered The coupling process is explained and the modeling requirements implied by the lightning environment are discussed The description of models selected and implemented is given Author N82-29996# Systems Control, Inc . Palo Alto, Calif SYSTEM IDENTIFICATION OF NONLINEAR AERODYNAM- IC MODELS T L Trankle, J H Vincent, and S N Franklin In AGARD Advan in the Tech and Technol of the Appl of Nonlinear Filters and Kalman Filters Mar 1982 26 p refs (For primary document see N82-29989 20-64) Avail NTIS HC A23/MF A01 System identification, a technology for determining a mathematical model of a dynamic system from observations of its response to inputs is discussed Identification technology is used for the determination of nonlinear aerodynamic models for aircraft maneuvering at high angles of attack The method outlined here (equation error, output error, and maximum likelihood algorithms) can directly nonlinear aerodynamic coefficients in table look-up or multivanable spline formats For application to nonlinear problems, the basic algorithms are enhanced by recent techniques for evaluation of partial derivatives of the likelihood function, calculation of parameter estimation uncertainties, and by the use of multidimensional splines as a generic model structure An example application of these methods to the identification of F-4S fighter aircraft high angle of attack aerodynamics is illustrated B W N82-30013*# National Aeronautics and Space Administration Ames Research Center. Moffett Field Calif APPLICATIONS TO AERONAUTICS OF THE THEORY OF TRANSFORMATIONS OF NONLINEAR SYSTEMS George Meyer, Renjeng Su, and L R Hunt May 1982 13 p refs (Contract N00014-76-C-1136) (NASA-TM-84249, NAS 11584249 A-8943) Avail NTIS HC A02/MF A01 CSCL 12B The development of the transformation theory is discussed Results and applications concerning the use of this design technique for automatic flight control of aircraft are presented The theory examines the transformation of nonlinear systems to linear systems The tracking of linear models by nonlinear plants is discussed Results of manned simulation are also presented B W N82-30029# Federal Aviation Administration, Washington. D C ESTIMATED AIRPLANE NOISE LEVELS IN A WEIGHED DECIBELS 11 Feb 1981 19 p refs (AC-36-3B) Avail NTIS HC A02/MF A01 Listings of estimated airplane noise levels in units of A-Weighted Sound Level in decibels (dBA) are provided NW N82-30030*# General Electric Co, Cincinnati. Ohio Aircraft Engine Group FORWARD VELOCITY EFFECTS ON FAN NOISE AND THE SUPPRESSION CHARACTERISTICS OF ADVANCED INLETS AS MEASURED IN THE NASA-AMES 40 BY 80 FOOT WIND TUNNEL Final Report Michael T Moore May 1980 161 p refs (Contract NAS2-8675) (NASA-CR-152328. NAS 126152328. R79AEG626) Avail NTIS HC A08/MF A01 CSCL 20A Forward velocity effects on the forward radiated fan noise and on the suppression characteristics of three advanced inlets relative to a baseline cylindrical inlet were measured in the NASA Ames Research Center 40 x 80 foot Wind Tunnel A modified JT15D turbofan engine in a quiet nacelle was the source of fan noise, the advanced mlpfs were a Conventional Takeoff/Landing (CTOL) hybrid inlet, a Short Takeoff/Landing (STOL) hybrid inlet, and a treated deflector inlet Also measured were the static to flight effects on the fan noise of canting the baseline inlet 4 deg downward to simulate typical wing mounted turbofan engines The CTOL hybrid inlet suppressed the high tip speed fan noise as much as 18 PNdB on a 61 m (200 ft) sideline scaled to a CF6 size engine while the STOL hybrid inlet suppressed the low tip speed fan noise as much as 13 PNdB on a 61 m (200 ft) sideline scaled to a OCSEE size engine The deflector inlet suppressed the high tip speed fan noise as much as 13 PNdB at 61 m (200 ft) overhead scaled to a CF6 size engine No significant changes in fan noise suppression for the CTOL and STOL hybrid inlets occurred for forward velocity changes above 21 m/s (68 ft/s) or for angle of attack changes up to 15 deg However, changes in both forward velocity and angle of attack changed the deflector inlet noise unpredictably due to the asymmetry of the inlet flow field into the fan Author N82-30031# Aerospace Medical Research Labs, Wright- Patterson AFB, Ohio USAF BIG-ENVIRONMENTAL NOISE DATA HANDBOOK. VOLUME 148 T-37B IN-FLIGHT CREW NOISE Harald K Hille Nov 1981 15 p (AF Proj 7231) (AD-A1 14943 AMRL-TR-75-50-Vol-148) Avail NTIS HC A02/MF A01 CSCL 01/2 The T-37B is a USAF two-seat primary trainer aircraft This report provides measured data defining the bioacoustic environ- ments at flight crew/passenger locations inside this aircraft during normal flight operations Data are reported at one location for 19 different flight conditions and psychoacoustic measures overall and band sound pressure levels. C-weighted and A-weighted sound levels, preferred speech interference level, perceived noise level, and limiting times for total daily exposure of personnel with and without standard Air Force ear protectors , GRA N82-30032# Aerospace Medical Research Labs. Wright- Patterson AFB. Ohio FAR-FIELD ACOUSTIC DATA FOR THE TEXAS ASE, INC HUSH HOUSE Robert A Lee Apr 1982 287 p refs (AF Proj 7231) (AD-A114564. AFAMRL-TR-81-148) Avail NTIS HC A13/MF A01 CSCL 01/2 This report supplements AFAM R L-TR-73-1 1 0, which describes the data base (NOISEFILE) used in the computer program (NOISEMAP) to predict the community noise exposure resulting from military aircraft operations The results of field test measurements to define the single-event noise produced on the ground by military aircraft/engines operating in the Texas ASE Inc hush-house are presented as a function of angle (0 deg to 180 deg from the front of the hush-house) and distance (200 ft to 2500 ft) in various acoustic metrics All the data are normalized to standard acoustic reference conditions of 59 F 540 N82-30261 temperature and 70% relative humidity Refer to Volume I of the AFAMRL-TR-73-110 report for discussion of the scope limitations, and definitions needed to understand and use the data in this report GRA N82-30261# Office National d'Etudes et de Recherches Aerospatiales. Pans (France) WIND TUNNEL STUDIES OF STORE SEPARATION WITH LOAD FACTOR. FREEDROPS AND CAPTIVE TRAJECTOR- IES c02 J Coste and J Leynaert In its La Rech Aerospatiale, Bi-monthly Bull no 1982-1. Jan-Feb 1982 (ESA-TT-755) May 1982 p 1-9 refs Transl into ENGLISH from La Rech Aerospatiale. Bull Bimestnel (Pans). No 1982-1. Jan-Feb 1982 (For primary document see N82-30260 20-99) Avail NTIS HC A02/MF A01, original report in FRENCH available at ONERA. Pans FF 55 Techniques used to study separation trajectories of stores dropped from under an aircraft are described In dropping tests, light, heavy and intermediate scaling laws which respect the Mach number are studied The captive trajectory tests use a six degrees of freedom system which moves the model step by step in the aerodynamic field of the aircraft Aerodynamic forces acting on the store are measured by an internal balance This method does not take into account the relative speed of store and aircraft Arrangements used to compensate for this defect are shown When the stores are inert, have perturbed trajectories, high initial separation speeds, or are incompatible with an external mount and an internal balance, the freedrop method is preferable, particularly for short trajectories In the contrary cases, or when the store is propelled, the captive trajectory method is essential For long trajectories, with several phases, the two methods are used in conjunction Author (ESA) 541 SUBJECT INDEX AERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 154) Typical Subject Index Listing NOVEMBER 1982 SUBJECT HEADING) AITIICIBG ADDITIVES pIcing tunnel tests of a composite porous leading edge for use with a liquid anti-ice system -Lewis icing research tunnel [HASA-CH-164966] H82-11052 The title is used to provide a description of the subject matter When the title is insufficiently descriptive of the document content, a title extension is added, separated from the title by hyphens The NASA or AIAA accession number is included in each entry to assist the user in locating the abstract in th3 abstract section of this supplement If applicable, a report number - o included as an aid in identifying the document 4-10 AIBCBAFI Manual reversion flight ccntrol system for A-10 aircraft: Pilot performance and simulator cue effects [AD-A113463] 1182-28302 1-300 AIBCBAF1 Gust load alleviation on Airbus A 300 482-1(0881 The effect of intake flow disturbances on AFO compressor blade higa cycle fatigue an the Airbus A300 A82-U0983 ABILITIES Human capabilities and limitations in systems N82-29297 ABLA1IVE HATEBIiLS Fireworthiness of transport aircraft interior systems N82-29284 AC GEHEBATOBS Hodels for the motor state of VSCF aircraft electrical power system Variable Speed Constant Frequency A82-40982 ACCE1EBOHETEBS Lou cost development of INS sensors for expendable £FV control and navigation [ AD-A112691] 1182-28291 ACCIDEHT PBEVEHIIOH A study of wind shear effects on aircraft operations and safety in Australia [ABL-SYS-BEPI-24] 882-28265 ACCIDJBBTS Fuel system protection methods H82-29283 ACOUSTIC ATTEMUATIOH The effect of barriers on wave propagation phenomena: With application for aircraft noise shielding [HASA-CB-169128] 1182-29111 ACOUSTIC EHISSIOB 'Listening1 systems to increase aircraft structural safety and reduce costs A82-39539 ACOUSTIC SIHOLAIIOH QCSEE over-the-wing eujine acoustic data [HASA-TH-82708] S82-29324 ACBOBATICS Sport aircraft Bussian took A82-40483 ACTIVE COSIBOL Estimation of the peak count of actively controlled aircraft A82-38447 CJ6 -jet engine performance improvement: High pressure turbine active clearance control [NASA-CB-165556] H82-28297 ADAPTIVE COSIBOL Adaptive fuel control feasibility investigation A82-40519 ADAPTIVE FILfEBS Adaptive filtering for an aircraft flying in turbulent atmosphere A82-38441 Research on an adaptive Kalman filter for solving the radar tracking problem German thesis A82-40562 AEBIAL BECOBHAISSAHCE Opto-eiectronical push-broom scanners for navigation, reconnaissance and generation of digital data bases A82-39747 Geophysical flight line flying and flight path recovery utilizing the Litton LIN-76 inertial navigation system [DE82-005555] H82-29292 AEBIAL BDDDEBS Design, fabrication and gualification of the T-2 composite rudder A82-39894 lEBOiCOfJSIICS The prediction of helicopter rotor discrete freguency ucise A82-40553 helicopter model scale results of blade-vortex interaction impulsive noise as affected by blade planform A82-40556 The effect of barriers on wave propagation phenomena: with application for aircraft noise shielding [BASA-CB-169128] N82-29111 Some comments on the prediction of forward flight effects on jet noise [HPIS-20/1981 ] N82-29118 AEBODxNAHIC B1LAHCE The use of a multi-degree-of-freedom dual balance system to measure cross and cross-coupling derivatives [AD-A114813] 1182-29333 AEHODYBAHIC CHABACIEHISTICS Aerodynamic characteristics of a large-scale, twin tilt-nacelle V/STOl model [AIAA PAPER 81-0150] A82-38443 Symposium on Flows with Separation, Stuttgart-, West Gernacy, November 23-25, 1981, Beports A82-38781 Supersonic missile aerodynamic and performance relationships for low observables mission profiles [ A I A A PAPEB 82-1298] A82-39085 An estimation of aerodynamic forces and moments on an airplane model under steady state spin conditions f A I A A PAPEB 82-1311] A82-39092 High angle-of-attack characteristics of a forward-swept wing fighter configuration [AIAA PAPEB 82-1322] A82-39099 Optimal three-dimensional turning performance of supersonic aircraft [AIAA PAPEB 82-1326] A82-39103 Unique flight characteristics of the AD-1 oblique-Ming research airplane [AIAA PAPEB 82-1329] ' A82-39106 A-1 AEBODT.BAHIC COEFFICIENTS SUBJECT INDEX Use of rotary balance dad forced oscillation test data in six degrees of freedom simulation [4I4A PAPEB 82-1364] A82-39129 NASA Dryden's experience in parameter estimation and its uses in fligat test [AIAA PAPEB 82-1373] A82-39135 Effects of vortex breakdown on longitudinal and lateral-directional aerodynamics of slender wings by the suction analogy [AIAA PAPEB 82-1385] A82-39141 The unsteady motion of a Ming traveling at subsonic speed above a (lane A82-39358 The rectangular wing with seoiinfinite span in nonlinear theory A82-39359 Optimal control application in supersonic aircraft performance 482-39374 Aerodynamic aspects of aircraft dynamics at high angles of attack /AGABD lecture/ [AIAA PAPEE 82-1363] A82-39836 Advanced aerodynanic dasign for future combat aircraft A82-40879 Some aerodynamic/flightmechanic aspects for the design of future coaxat aircraft A82-40880 Recent advances in the performance of high bypass ratio fans A82-4C891 Aerodynamic develofment of laminar flow control on swept wings using distributed suction through porous surfaces 482-40894 Viscous transonic airfoil flow simulation 482-40897 Deternination of airplane aerodynamic parameters from flight data at aigh angles of attack 482-40928 Aerodynamic concepts for fuel-efficient transport aircraft 482-40957 Variable geometry aerofoils as applied to the Beatty B-5 and B-6 sailplanes 482-40968 Aircraft design for fuel efficiency 482-40973 Advanced aerodynamic wing design for commercial transports - Beview cf a technology program in the Netherlands A82-40985 Becent airfoil developments at DFV1B A82-40986 fling-tip ]ets aerodynamc performance A82-40987 An experimental investigation of leading-edge spanwise bloving A82-40988 Vortex formation over double-delta wings A82-40989 Hind tunnel test and aerodynamic analysis of three aeroelastically tailored wings A82-41001 Upper Vortex Flap - A tersatile surface for highly swept wings A82-41002 An initial look at the supersonic aerodynamics of twin-fuselage aircraft concepts A82-41008 Low-speed characteristics of a fighter-type configuration at higj angles—of-attack and sideslip A82-41020 Hind-tunnel investigation cf a full-scale canard-configured general aviation aircraft A82-41024 A summary of V/STOL inlet analysis methods [HASA-TH-82885] 1182-28249 Nearfield aerodynamics and optical propagation characteristics of a large-scale turret model [AD-A113910] H82-28624 Aerodynamics of an airfoil with a jet issuing from its surface [SASA-TH-84825] 882-29267 AEBODIBAHIC COEFFICIENTS Analytical study of vortex flaps on highly swept delta wings A82-41003 Fuselage effects in leading edge vortex flap aerodynamics 482-41006 Prelaunch estimates of near Earth satellite lifetimes using quasi-dynamic atmosphere models - application to a proposed Brazilian satellite [INPE-2325-PBE/080] N62-29347 AEBODIHAHIC COHFI6UBATIOHS An experimental investigation of a bearingless model rotor in hover A82-40512 Computer enhanced analysis of a jet in a cross-stream N82-29555 AEBODIHAHIC DBAG An evaluation of vertical drag and ground effect using the BSB4 rotor balance system Botor Systems Besearch Aircraft 482-40510 Development of an advanced no-moving-parts high-lift airfoil 482-40971 Spanwise distribution of vortex drag and leading-edge suction in subsonic flow 482-41005 Optimization of canard configurations - An integrated approach and practical drag estimation method A82-41023 Hinimum induced drag of canard configurations 482-41116 AEEODIBABIC FOBCES An estimation of aerodynamic forces and moments on an airplane model under steady state spin conditions [AIAA PAPEB 82-1311] 482-39092 lateral aerodynamics of delta wings with leading edge separation [AIA4 P4PEB 82-1386] 482-39142 Inlet and airframe compatibility for a V/STOL fighter/attack aircraft with top-mounted inlets 482-40908 Aerodynamic interactions between a 1/6-scale helicopter rotor and a body of revolution 482-40947 Beduced nonlinear flight dynamic model of elastic structure aircraft 482-41009 Aerodynamic interactions between a 1/6 scale helicopter rotor and a body of revolution [S4S4-TH-84247] N82-28252 AEBODI11BIC INTEBFEBENCE The use of small strakes to reduce interference drag of a low wing, twin engine airplane [AIAA EAPEB 82-1323] A82-39100 Summary of sting interference effects for cone, missile, and aircraft configurations as determined by dynamic and static measurements [AIAA PAPEB 82-1366] 482-40395 External aerodynamic design for a laminar flow control glove on a Lockheed JetStar wing A82-40895 Computational and experimental studies of light twin aerodynamic interference A82-40930 Evaluation of an experimental technigue to investigate tne effects of the engine position on engine/pylon/wing interference wind tunnel tests [NLB-HP-81020-U] N82-28262 AEBODIMABIC LOADS Supersonic missile aerodynamic and performance relationships for low observables mission profiles [4144 PAPEB 82-1298] A82-39085 Dynamic load measurements with delta wings undergoing self-induced roll-oscillations [AIAA PAPEB 82-1320] 482-39098 Haneuver stability of a vehicle with a towed body [AIAA PAPEB 82-1347] 482-39119 The use of linearized-aerodynamics and vortex-flow methods in aircraft design /invited paper/ [AIAA P4PEB 82-1384] 482-40294 Theory and application of optimum airloads to rotors in hover and forward flight 482-40506 Performance of the Botor Systems Besearch Aircraft calibrated rotor loads measurement system 482-40549 4-2 SUBJECT IHDEX AIB TO AIB HISSI1ES Eesults of the AH-61 structural Demonstration A82-40551 Gust load alleviation on Airbus A 300 &S2-40SS1 Investigation of the unsteady airloads on a transport aircraft type airfoil with two interchangeable oscillating trailing edge flaps, at transonic speed and high Reynolds numbers A82-40909 A crack growth model under spectrum loading A82-40961 Determination of load spectra and their application for keeping the operational life proof of sporting airplanes £82-41010 The role of the scale parameter in service load ,, assessment and simulation of aircraft flight A82-41011 Beans for controlling aerodynamically induced tvist [HASA-CASE-LAB-12175-1] 882-28279 B747/JT9D flight loads and their effect on engine running clearances and performance deterioration; BCAC SAI1/P and HA J19D engine diagnostics programs [NASA-CB-165573] 1182-28296 AEBODIHAHIC BOISE The effect of harriers on nave propagation phenomena: With application for aircraft noise shielding [HASA-CB-169128] N82-29111 AEBODIBAB1C SliEIUJI Flight-determined correction terms for angle of attack and sideslip [AIAA PAPEE 82-1374] A82-40290 AEHODTBAHIC STilllBG Analytic extrapolation to full scale aircraft dynamics £AIAA PAPES 82-1387] A82-39143 Dynamic surface oeasureoents on a model helicopter rotor during blade slap at high angles of attack A82-40555 Prediction of high alpaa flight characteristics utilizing rotary balance data A82-40953 AEBODIH1HICS International Council at the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, HA, August 22-27, 1S62, proceedings. Volumes 11 £ 2 A82-40876 Aerodynamic research applications at Boeing A82-41000 General aviation activity and avionics survey [AD-A112924] H82-28244 Aerodynamics of advanced axial-flow turbomachinery [AD-.A114911] B82-29328 AEBOELAS1ICITY Eobust Kalman filter design for active flutter suppression systems A82-38442 Dynamic stability of flexible forward swept wing aircraft £AIAA PAPEB 82-1325] A82-39102 Summary and recent results from the BASA advanced high-speed propeller research program [AIAA PAPEE 82-1119] A82-40419 An experimental investigation of a iearingless model rotor in hover A82-40512 Helicopter vibration reduction by rotor blade modal shaping A82-40514 Finite element analysis for bearingless rotor blade aeroelasticity A82-40517 Calculations of transonic steady state aeroelastic effects for a canard airplane A82-40882 Computer-aided derivation cf eguations of motion for rotary-wing aeroaiastic problems A82-40883 Design of compensated flutter suppression systems A82-40904 Bind tunnel test and aerodynamic analysis of three aeroelastically tailored vings A82-41001 Hind-tunnel evaluation of an aeroelastically conformable rotor [AD-A114384] N82-28260 Design considerations and experiences in the use of composite material for an aeroelastic research wing [MASA-Tfl-83291] B82-28280 ABBOiAUIICS International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, HA, August 22-27, 1982, Proceedings. Volumes 11 6 2 A82-40876 AEBOSPACE BBGIIEEBIIG International Council of the Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and Technology Conference, Seattle, HA, August 22-27, 1982, Proceedings. Volumes 11 6 2 182-40876 ABBOSP4CB SISTEflS CDS-the designer's aedia, the analyst's model -— Configuration Developaent System for aircraft A82-40991 Optimizing aerospace structures for manufacturing cost A82-41014 ABBOSPACEPLAiES Inflated vings A82-40966 A6BICOLTOBAI AIBCBAFT Bationalization of the maintenance process for helicopter Ka-26 A82-39246 The design integration of wingtip devices for light general aviation aircraft A82-40933 Agricultural airplane mission time structure Characteristics fMASA-TB-84470] • M82-29329 AH-16 HE1ICOPTEB Error minimization in ground vibration testing of helicopter structures A82-40550 AB-64 BE1ICOP1EB Structural design of a crashworthy landing gear for the AH-64 Attack Helicopter A82-40547 Besults of the AH-64 Structural Demonstration A82-40551 AIB DEFUSE Logistics research program in the United states Air force A82-40963 AIB FLOS Fluctuating forces and rotor noise due to distorted inflow A82-40945 Hind-tunnel testing of V/STOL configurations at high lift A82-40949 AIB LAB Boise pollution and airport regulation A82-40051 O'Hare International Airport - Impervious to proposed state efforts to limit airport noise A82-40052 AIB HAVIGATIOB Opto-electronical push-broom scanners for navigation, reconnaissance and generation of digital data bases A82-39747 Low cost development of IBS sensors for expendable HPV control and navigation CAD-A112691J ' S82-28291 AIB POLIDTI01 Smoke abatement system for crash rescue/fire training facilities fAD-A114380] H82-28268 AIB QOALIT7. Atmospheric chemistry of hydrocarbon fuels. Volume 2: Outdoor chamber data tabulations. Part 1 [AD-4113665] N82-28842 AIB TO AIB BISSIIES Air-to-air missile avoidance £AIAA 82-1516] A82-38939 Algorithm development for infra-red air-to-air guidance systems A82-39191 A-3 AIB 10 SDBF1CE HISSILKS SUBJECT IIDEX 1IB TO SOBFACB HISSILES Target acquisition system/air-to-surface weapon compatibility analysis [AIAA 82-1618] A82-38995 1IB TRAFFIC COHTBOL Complete flexibility and realism in radar simulation A82-38461 Future terminal area systems A 82-3 84 62 Fuel conservation: The airline - A1C A82-38464 Analysis of general-aviation accidents using ATC radar records [AIAA PAPEB 82-1=10] A82-39091 Analysis of in-trail fcllciiing dynamics of CDTI-equipped aircraft Cockpit Displays of Traffic Information [AIAA PAPEB 82-1330] A82-39107 H4SA/FAA Helicopter ATC simulation investigation of BNAV/HLS instrumeat approaches A82-40535 A concept for ID-guidance ct transport aircraft in the 1HA terminal Maneuvering Area A82-40942 Estimation of the number of in-flight aircraft on instrument flight rules A82-41117 Electronic/electric technology benefits study avionics [NASA-CB-165890] H82-28243 computer outages at air terminal facilities and their correlation to near miss mid-air collisions (AFMD-82-43) [B-206064] B82-28264 A study of wind shear effects on aircraft operations and safety in Australia [ABL-SYS-BEP3-24] H82-28265 Special investigation report: Air traffic control system [PB82-136276] S82-28277 FAA aviation forecasts-fiscal years 1982-1993 [AD-A114696] H82-29261 Terminal information display system benefits and costs [A0-A114937] B82-29291 Human factors in air t raff ic control [AGABD-AG-275] N82-29293 The air traffic control system B 82-2 92 94 Human factors contributions to air traffic control systems H82-29295 Han as a system component B82-29296 Human capabilities and -luitations in systems H82-29297 Jobs and tasks in air traffic control N82-29298 The work environment K82-29299 Displays , H82-29300 Controls N82-29301 Communications 882-29302 Additional functions within the air traffic , control system B82-29309 Future trends and problems N82-29310 Cloving target detector (Mod 2) [AD-A114709] 882-29520 AIB TBAFFIC COBIBOLLEBS (fJESOBSEI) Human factors in air traffic control [AGABD-AG-275] M82-29293 The air traffic control system B82-29294 Man as a system component N82-29296 Jobs and tasks in air traffic control N82-29298 AIBBOBHE BCpIPHEBT . , Application of an, optical data link ii. the airborne scanning systea \^ A82-39275 Multifunction multiband airborne radio architecture study [AD-A114427] H82-28523 Baseline sonitoring using aircraft laser ranging spaceborne laser simulation and aircraft laser tracking [HASA-Tfl-73298] 1182-28690 AIBBOBHE BADAB APPBOACH Flight test evaluation of a video tracker for enhanced offshore airborne radar approach capability A82-40531 AIBBOEHE/SPACEBOBSE COMPUTERS Estimation of the peak' count of actively controlled aircraft A82-38447 PHCS - A commercial flight management computer system [AIAA 82-1515] A82-38938 A preliminary laboratory evaluation of a reconfigurable integrated flight control concept [AISA 82-1597] A82-38982 An MLS with computer aided landing approach [ A I A A PAPEB 82-1352] A82-39122 Flight management computers A82-39321 The fourth dimension flight management system for airline operations A82-39540 The control and guidance unit for HACHAM A82-39738 Boeing's new 767 eases crew workload A82-40348 Aircraft design for fuel efficiency A82-40973 Investigations concerned with shifting pilot activities to a higher hierarchical stage of flight control German thesis A82-41453 Advanced aircraft electrical system control technology demonstrator. Phase 1: Analysis and preliminary design [AD-A113633] B82-28284 Problems related to the integration of fault tolerant aircraft electronic systems [HASA-CB-165926] B82-29022 AIBCB4FT Fuel system protection methods M82-29283 AIBCBiFT ACCIDEHTS Analysis of general-aviation accidents using ATC radar records [AIAA PAPEB 82-1310] A82-39091 Smoke abatement system for crash rescue/fire training facilities [AD-A114380] B82-28268 Flight attendant injuries: 1971-1976 [AD-A114909] " N82-29274 Crashwortniness studies: Cabin, seat, restraint, and injury findings in selected general aviation accidents [AD-A114878] N82-29275 Annual review of aircraft accident data: OS general aviation calendar year 1979 [PB82-136250] B82-29278 Aircraft post crash fire redaction/survivability enhancement from a manufacturer's viewpoint B82-29286 Aircraft post-crash fire fighting/rescue H82-29287 AIBCBIFT AITEIBAS Monopole antenna patterns on finite size composite ground planes in aircraft A82-41055 Delta electrical load analysis C-141B JACC/CP aircraft [AD-A113761] B82-28283 AIBCBiFT APPBOACH SPACING Analysis of in-trail following dynamics of CDTI-eguipped aircraft Cockpit Displays of Traffic Information [AIAi PAPEB 82-1330] A82-39107 AIBCBAFT BBAKES Alert aircraft roll over chocks [AD-A107456] B82-28307 AIRCBAFT COflMOHICATIOB Digital computer simulation of modern aeronautical digital communication systems A82-4094Q Propagation problems associated with aircraft communications systems N82-29535 4-4 SUBJECT INDEX AIBCBAFT CO8TBOL AIBCBAFT COBPABIHBBTS Crashworthiness studies: Cabjui, seat, restraint, and injury findings in selected general aviation accidents [AD-A114878] 1182-29275 Fireworthiness of transport aircraft interior systems N82-29284 OSAF bioenvironmental noise data handbook. Volume 148. T-37B in-flight crew noise [AD-A114943J M82-30031 AIECUAFT COHFIGOBATIOUS High angle-of-attack characteristics of a forward-swept wing fighter configuration [AIAA PAPEE 82-1322] A82-39099 Stabileye. B, Stephenson EPV perforaance, design and materials characteristics A82-39733 Summary of sting interference effects for cone, missile, and aircraft configurations as determined by dynamic and static measurements [AIAA PAPEB 82-1366] A82-40395 An evaluation of vertical drag and ground effect using the ESBA rotor balance system Botor Systems Besearch Aircraft A82-110510 The ZAH-64 empennage aad tail rotor - A technical history A82-40528 Bingfin augmentation effects A82-40548 Tail versus canard configuration - An aerodynamic comparison with regard to the suitability for future tactical combat aircraft A82-40901 Assessment of advanced technologies for high performance single-engine business airplanes A82-40932 Hind-tunnel testing of V/S1OL configurations at high lift A82-40949 Design integration of CCS/USB for a sea-based aircraft A82-40972 Perforaance characteristics of a buoyant quad-rotor research aircraft A82-40974 CDS-the designer's media, the analyst's model Configuration Development System for aircraft A82-U0991 Aircraft geometry verification with enhanced computer-generated displays A82-40992 An initial lock at the supersonic aerodynamics of twin-fuselage aircraft concepts A82-41008 Low-speed characteristics of a fighter-type configuration at high angles-of-attack and sideslip A82-41020 Aircraft geometry verification with enhanced computer generated displays [HASA-TH-84254J N82-29268 Annual review of aircraft accident data: OS general aviation calendar year 1979 [PB82-136250] N82-29278 Development cf flying qualities criteria for single pilot instrument flight operations [HASA-CB-165932] N82-29288 AIBCBAFT COHSIBOCIIOH HATIfililS Composite use on helicopters A82-38222 Toward all-ccmposite haliccpter fuselage A82-38223 Committing composites to the Boeing 767 A82-38224 The effect of hybrid composite materials on the dynamic characteristics of helicopter rotor blades A 82-3 92 63 The technological aspects of titanium application in the 10-111 aircraft structure A82-39718 Stabileye. B. Stephenson EPV performance, design and materials characteristics A82-39733 She national dynamics 'observer' mini-BPV for tropical operation A82-39734 On the state of technology and trends in composite materials in the United States A82-39882 Tests of CFBP spar/rib models with corrugated web A82-39890 Evaluation of CFBP prototype structures for aircraft A82-39892 Developments on graphite/epoxy T-2 nose landing gear door A82-39893 Fabrication of CFEP prototype structure for aircraft horizontal tail leading edge slat rail A82-39896 Development status of a composite vertical stabilizer for a jet trainer (A82-39897 In-plane shear test of thin panels A82-40545 A summary of weight savings data for composite V5101 structure A82-40546 Material and process developments on the Boeing 767 A82-40902 The promise of laminated metals in aircraft design A82-40903 Material identification for the design of composite rotary wings A82-40937 Application of a new hybrid material /AEALL/ in aircraft structures A82-U0975 Design and fabrication of cocured composite hat-stiffened panels A82-40978 Technical and economic comparison of carbon fiber tape and woven fabric applications A82-40993 Application of composite materials and new design concepts for future transport aircraft A82-40994 Composite structures repair A82-41015 Honopole antenna patterns on finite size composite ground planes in aircraft A82-41055 AIBCBiFI COBTEOL Adaptive filtering for an aircraft flying in turbulent atmosphere A82-38441 Estimation of the peak count of actively controlled aircraft A82-38447 Pilot models for discrete maneuvers [AIAA 82-1519] A82-38940 Design and flight testing of digital direct side-force control laws [AIAA 82-1521] A82-38941 The effects of the delays on systems subject to manual control A82-38943 Modal control of relaxed static stability aircraft [AIAA 82-1524] A82-38944 An X-Sing aircraft control system concept [AIAA 82-1540] . A82-38954 A design criterion for highly augmented fly-ty-wire aircraft [AIAA 82-1570] A82-38969 The use of differential pressure feedback in an automatic flight control system [AIAA 82-1596] A82-38981 The ideal controlled element for real airplanes is not K/s [AIAA 82-1606] A82-38986 An alternate method of specifying bandwidth for flying gualities [ (AHA 82-1609] A82-38988 Investigation of low order lateral directional transfer function models for augmented aircraft [AIAA 82-1610] ' A82-38989 An analysis of a nonlinear instability in the implementation of a VIOL control system during hover [AIAA 82-1611] A82-38990 X-29A flight control system design experiences [AIAA 82-1538] A82-39003 The effects of atoospheric turbulence on a guadrotor heavy lift airship [AIAA 82-1542] A82-39009 4-5 AIBCBAFT DESIGN SUBJECT INDEX Flight control synthesis using robust output observers [(4144 82-1575] 482-39016 Handling qualities criteria for flight path control of V/STO1 aircraft £4144 PAPEB 82-1292] 482-39081 Piloted simulator evaluation of a relaxed static stability fighter at nigh angle-cf-attack [4144 P4PEB 82-1295] 482-39082 In-Flight investigation of large airplane flying qualities for approach and landing £4144 P4PEE 82-1296] 482-39083 Parameter estmaticn applied to general aviation aircraft - 4 case stuiy [AIAA P4PEB 82-1313] 482-39094 Flight dynamics of rotorcraft in steep high-g turns [&IAA P&PEE 82-1345] 482-39117 Guidance for the use oi equivalent systems with BIL-F-8785C for aircraft flight control systems [4IA4 PAPEB 82-1355] A82-39124 4 modern approach to pilot/vehicle analysis and the Neal-Siith criteria [4IAA P4PEB 82-1357] A82-39125 Electronic stabilization cf an aircraft 482-39322 Optimal control application in supersonic aircraft performance 482-39374 Flying qualities requirements for roll C4S systems [AIAA PAPEB 82-1356] A82-40287 Terrain following/terrain avoidance system concept development [AIAA PAPEB 82-1518] 482-40428 Flight experience with a backup flight-control system for the HiHAT research vehicle [AIAA PAPEB 82-1541] 482-40429 Optimal open-loop aircraft control for go-around maneuvers under wind shear influence A82-40943 Hind tunnel measurements of longitudinal stability and control characteristics of primary and secondary wing configurations 482-41025 4 study of wind shear alf£Cts on aircraft operations and safety in Australia [ABL-STS-BIP1-24] N82-28265 Evaluations of helicopter instrument-flight handling qualities [AD-A114004] S82-28285 Analytical and simulator study of advanced transport £N4S4-CB-3572] N82-28298 Manual reversion flight control systeu for 4-10 aircraft: Pilot performance and simulator cue effects [4D-A113463] 1182-28302 AIBCBAFT DESIGH Forward-swept wings adl supersonic zip 482-38216 Mirage 2000 - lowards possible high series production aircraft 482-38249 JVX, what an opportunity Joint Services Advanced Vertical lart Aircraft Program A82-38423 Aerodynamic characteristics of a large-scale, twin tilt-nacelle V/STOL model [AIAA PAPEE 81-0150] A82-38443 The use of small strakas to reduce interference drag of a low wing, twin engine airplane [AI44 P4PEE 82-1323] 482-39100 Dse of rotary balance and forced oscillation test data in six degrees cf freedom simulation [4144 PAPEB 82-1364] 482-39129 Bemotely piloted vehicles; International Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Papers and Supplementary Papers 482-39727 Horses for courses in iP¥ operations system components design anj development in terms of performance and cost 482-39729 Canadair rotary wing technology development 482-39731 Stabileye. B. stephenscn BPV performance, design and materials characteristics 482-39733 BACH4N - 4 unmanned aircraft flight research facility 482-39735 Electric propulsion for a mini BPV system 482-39744 Development of the advanced composite ground spoiler for C-1 medium transport aircraft 182-39895 Ihe use of linearized-aerodynamics and vortex-flow methods in aircraft design /invited paper/ [4144 PAPEB 82-1384] 482-40294 Analytical design and validation of digital flight control system structure [AIAA PAPEB 82-1626] 482-40434 Predesign study for an advanced flight research rotor A82-40525 4 summary of weight savings data for composite VSTOI structure 482-40546 Engineering aspects of international collaboration on Tornado 482-40878 Advanced aerodynamic design for future combat aircraft 482-40879 Some aerodynaiic/fligbtmechanic aspects for the • design of future combat aircraft 482-40880 Application of advanced exhaust nozzles for tactical aircraft 482-40889 Observations and implications of natural laminar flow on practical airplane surfaces 482-40893 External aerodynamic design for a laminar flow control glove on a Lockheed Jetstar wing 482-40895 Material and process developments on the Boeing 767 482-40902 The promise of laminated metals in aircraft design 482-40903 Design of compensated flatter suppression systems A82-40904 Dual wing, swept forward swept rearward wing, and single wing design optimization for high performance business airplanes 482-40931 The design integration of wingtip devices for light general aviation aircraft 482-40933 Operation 71 OF - Development of a composite material wing 482-40934 Non-honeycomb F-16 horizontal stabilizer structural design 482-40936 Progress at Douglas on laminar flow control applied to commercial transport aircraft 482-40958 Design and tests of airfoils for sailplanes with an application to the" ASH-19B 482-40967 Ejector powered propulsion and high lift subsonic wing A62-40970 Design integration of CCH/OSB for a sea-based aircraft 482-40972 Aircraft design for fuel efficiency A82-40973 Advanced aerodynamic wing design for commercial transports - Beview of a technology program in the Netherlands 482-40985 Becent airfoil developments at DFVLB A82-40986 CA1IA - 4 computer aided design and manufacturing tridimensional system 482-40990 CDS-the designer's media, the analyst's model Configuration Development System for aircraft 482-40991 Aircraft geometry verification with enhanced computer-generated displays 482-40992 Application of composite materials and new design concepts for future transport aircraft 482-40994 4-6 SUBJECT IIDEX AIBCBAFT LAHDIHG Rind tunnel test and aerodynamic analysis of three aeroelastically tailored vings A82-41001 Optimizing aerospace structures for manufacturing .cost 182-11014 King design for supersonic cruise/transonic maneuver aircraft 482-41021 Analysis of jet transport tings with deflected control surfaces by using a combination of 2- and 3-0 methods A82-41022 Optimization of canard configurations - in integrated approach and practical drag estimation method A82-11023 The determination of gust loads on nonlinear aircraft using a power spectral density approach[NLB-TB-80123-U] N82-28303 Aircraft geometry verification with enhanced computer generated displays [NASA-TH-84254] M82-29268 Automated optimum design of wing structures. Deterministic and probabilistic approaches[NASA-TM-84475] • H82-29317 AIBCBAFT EMG1IES The national dynamics 'observer' mini-EPV for tropical operation A82-39734 HASA research in supersonic propulsion - A decade of progress [AIAA PAPEE 82-10U8] A82-40417 Optimized 10 ton class commercial aircraft engine A82-40890 Preliminary design of an advanced integrated power and avionics infornation system A82-40907 Assessment of advanced technologies for high performance single-engine business airplanes A82-40932 The nonsynchronous whirls of the turbine rotor in aerojet engines A82-40944 Third generation turbo fans * A82-40964 Design integration of CCB/OSB for a sea-based aircraft A82-40972 The effect of intake flow disturbances on APO compressor blade hign cycle fatigue in the Airbus A300 A82-40983 Engine controls for the 1580s and 1950s A82-40984 Advances in high-speed rolling-element bearings [SASA-TS-82910] S82-28644 QCSEE over-the-wing engine acoustic data [HASA-TM-82708] N82-29324 Estimated airplane noise Jevels in i-weighed decibels [AC-36-3B] H82-30029 AIBCBAFT EQOIPMEHT Analysis of an airplane windshield anti-icing system[AIAA PAPEB 82-1372] A82-39134 Concept demonstration of automatic subsystem parameter monitoring military helicopter cockpit instruDentation A82-40530 Support of the HH-65A - The impact of advanced technology of VTOL systems upon existing product support A82-40541 Models for the motor state of VSCP aircraft electrical power system Variable Speed Constant Frequency 482-40582 A compendium of lightning effects en future aircraft electronic systems [AD-A114117] 882-28293 Feasibility study of a 270V dc flat cable aircraft electrical power distributed system •- [AD-A114026] N82-28S52 AIBCBAFT FUELS Fuel conservation: The airline - ATC A82-38464 Beguirements and trends in fuel consumption in transport mission with aircraft and surface vehicles A82-40956 Aerodynamic concepts for fuel-efficient transport aircraft A82-40957 An exploratory research and development program leading to specifications for aviation turbine fuel from whole crude shale oil. Part 1: Preliminary process analyses [AD-A112681] H82-28462 An exploratory research and development program leading to specifications for aviation turbine fuel from whole crude shale oil. Part 2: Process variable analyses and laboratory sample production [AD-A112682] N82-28463 An exploratory research and development program leading to specifications for aviation turbine fuel from whole crude shale oil. Part 3: Production of specification of JP-4 fuel from geokinetics shale oil [AD-A112683] N82-28464 Aircraft fire safety [AGABD-LS-123] H82-29279 Aircraft fire mishap experience/crash fire scenario guantitatiou N82-29280 Aviation fuels-future outlook and impact on aircraft fire threat N82-29282 The development and applications of a full-scale vide body test article to study the behavior of interior materials during a postcrash fuel fire N82-29285 The feasibility of a high-altitude aircraft platform with consideration of technological and societal constraints [NASA-TM-84508] N82-29313 AIBCEAFT GOIEASCE PHCS - A commercial flight management computer system [AIAA 82-1515] A82-38938 The control and guidance unit for MACHAS A82-39738 A terrain following system, an algorithm and a sensor A82-39740 Flight simulation studies on the feasibility of laterally segmented approaches in an MLS environment A82-40941 A concept for 4D-guidance of transport aircraft in the 1BA Terminal Maneuvering Area A82-40942 Investigations concerned with shifting pilot activities to a higher hierarchical stage of flight control German thesis A82-41453 AIBCBAFT HAZABDS The operation of aircraft and helicopters in difficult meteorological and environmental conditions Russian book A82-39295 AIBCBAFt HTDBAOLIC SYSTEMS Hydraulic Universal Display Processor System (HUDPS) [AD-A114428] M82-28294 AIBCBAFT IHSTBOHBHTS Evaluation of an automatic subsystem parameter monitor for aircraft A82-40552 AIBCBAFT LAHDIHG In-Flight investigation of large airplane flying qualities for approach and landing [AIAA PAPEE 82-1296] A82-39083 An KIS with computer aided landing approach [AIAA PAPEE 82-1352] A82-39122 Instrument landing systems /ILS/ at airports of the German Democratic Republic A82-39248 Touchdown technology large aircraft landing gear stress A82-40057 Flying quality reguirements for V/STOL transition [AIAA PAPEE 82-1293] A82-40276 A-7 ilfiCBAFT BAIBIEIAHCE SUBJECT IHDBI Visual scene simulation concerning the landing of sporting aircraft in connection wi th investigations regarding the conticl and learning behavior of the pilot German thesis A82-41447 Effects of approach lighting and variation in visible runway length cm perception of approach angle in simulated night landings [AD-A114742] H82-29290 AIBCBAFX H4IHTESAHCE D.s. Harine Corps 4V-8& aaintenance experience [4144 P4PEE 81-2£57] 482-38446 Rationalization of the maintenance process for helicopter Ka-26 A82-39216 Civil helicopter piopulsicn system reliability and engine monitoring technology assessments 482-40518 Age exploration in naval aviation Reliability Centered Maintenance program A82-40962 Composite structures repair 482-41015 Principles of achieving carnage tolerance with flexible maintenance programs for new and aging aircraft £82-41016 AIBCBAFX HAHEUVEBS Air-to-air missile avoidance [AIAA 82-1516] A82-38939 Pilot models for discrete maneuvers [AIAA 82-1519] A82-38940 Optimal three-dimensional turning performance of supersonic aircraft [AIAA PAPEE 82-1326] A82-39103 Maneuver stability of a vehicle with a towed body [AIAA PAPEE 82-1347] A82-39119 Flight-determined correction terns for angle of attack and sideslip [AIAA PAPEB 82-1374] A82-40290 Determination of airplane aerodynanic parameters from flight data at nigh angles of attack A82-40928 Optimal open-loop aircraft control for go-around maneuvers under wind shear influence 182-40943 King design for supersonic cruise/transonic maneuver aircraft A82-41021 AIBCBAFI BODELS Aerodynamic characteristics of a large-scale, twin tilt-nacelle V/S30L aodel [AIAA PAPEE 81-0150] A82-38443 An X-Hing aircraft control system concept [AIAA 82-1540] A82-38954 Investigation of low order lateral directional transfer function models for augmented aircraft [AIAA 82-1610] A82-38S89 An estimation of aerodynasic forces and moments on an airplane model unJer steady state spin conditions [AIAA PAPEE 82-1311] A82-39092 An investigation of scale nodel testing of VIOL aircraft in hover A82-40911 Seduced nonlinear fligat dynamic model of elastic structure aircraft A82-41009 An improved propulsion system simulation technique for scaled wind tunnei model testing of advanced fighters A82-41019 Hind-tunnel investigation of a full-scale canard-configured general aviation aircraft A82-41024 System identification of nonlinear aerodynamic models H82-29996 AISCBAFT BOISE Noise pollution and airport regulation 482-40051 O'Uare International Airport - Impervious to proposed state efforts to limit airport noise A82-40052 Helicopter model scale results of Hade-vortex interaction impulsive noise as affected by blade planforn A82-40556 Fluctuating forces and rotor noise due to distorted inflow A82-40945 Field studies of the Air Force procedures (NOISECHECK) for measuring community noise exposure f rom aircraft operations [AD-A113672] H82-28841 Estimated airplane noise levels in A-weighed decibels [AC-36-3B] N82-30029 Far-field acoustic data' for the Texas ASE, Inc. hush house [AD-A114564] H82-30032 AIBCBAFT PABTS The technological aspects of titanium application in the TO-144 aircraft structure A82-39718 Horses for courses in BPV operations system components design and development in terms of performance and cost A82-39729 AIECEAFI PEBFOBBABCB Hirage 2000 - Towards possible high series production aircraft A82-38249 Optimal 'three-dimensional turning performance of supersonic aircraft [AIAA PAPEE 82-1326] A82-39103 Analytic extrapolation to full scale aircraft dynamics [AIAA PAPEE 82-1387] A82-39143 Remotely piloted vehicles; International Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Papers and Supplementary Papers A82-39727 Horses for courses in BPV operations system components design and development in terms of performance and cost A82-39729 Canadair rotary wing technology development A 82-39731 Stabileye. B. Stephenson BPV performance, design and materials characteristics A82-39733 Aerodynamic aspects of aircraft dynamics at high angles of attack /AGABD Lecture/ [AIAA PAPEB 82-1363] A82-39836 Antisymmetric approach and landing thrust reverser impacts on usage and LCC life cycle cost A82-40892 Assessment of advanced technologies fof high performance single-engine business airplanes A82-40932 Performance characteristics of a buoyant guad-rotor research aircraft A82-40974 The role of the scale parameter in service load assessment and simulation of aircraft flight A82-41011 AIBCBAFT PI10IS The system of 'objective control' A82-39245 Boeing's new 767 eases crew workload A82-40348 A study of wind shear effects on aircraft operations and safety in Australia [ABL-SJS-BEPT-24] H82-28265 AIBCBAFT PBODUCTIOH Adaptation of pultrusion to the manufacture of helicopter components A82-40537 Design and fabrication of a composite rear fuselage for the DH-60 /Black Hawk/ A82-40544 A one-shot autoclave manufacturing process for carbon epoxy components 482-40935 Fatigue behavior of weldbonded joints A82-41115 International aviation (selected articles) [AD-A114422] H82-28245 &IRCBIFT PBODUCTIOB COSTS Optimizing aerospace structures for manufacturing cost A82-41014 AIBCBAFT BELIABILIi; Rationalization of the maintenance process for helicopter Ka-26 482-39246 A-8 SUBJECT INDEX AIRFOIL PBOFILES Civil helicopter propulsion system reliability and engine monitoring technology assessments A82-40518 Age exploration in navai. aviation Reliability Centered Maintenance program A82-40962 Recommended practice for a demonstration of nondestructive Evaluation /8DE/ reliability on aircraft production tarts - Introduction to the , guidelines 482-11110 AIBCBAFT SAFETY Complete flexibility and realism in radar simulation 482-38461 The detection of low level wind shear. II A82-38463 Rind shear - Its effect on an aircraft and ways to reduce the hazard. II 482-38500 'Listening1 systems to increase aircraft structural safety anJ reduce costs A82-39539 Touchdown technology large aircraft landing gear stress A82-40057 An evaluation cf helicopter autorotation assist concepts 482-10521* Flight attendant injuries: 1971-1S76 [AD-M14909] H82-29274 Aircraft fire safety [AGABD-LS-123] N82-29279 Aircraft fire mishap experience/crash fire scenario quantisation II82-29280 Human response to fire H82-29281 Aviation fuels-future outlook and impact on aircraft fire threat N82-29282 Fireworthiness of transport aircraft interior systems N82-29281 AIBCBAFT SPECIFICA1IOSS Perspectives of the flying qualities specification [AIAA PAPEE 82-1351;] A82-39123 Flying gualities reguirenents for roll CAS systems [AIAA PAPER 82-1356] A82-10287 Sport aircraft Russian book A82-10483 AIRCRAFT SPIH Applications of parameter estimation in the study of spinning airplanes [AIAA PAPEE 82-1309] A82-39090 AIBCBAFT STABILITY Simulator investigations of various side-stick controller/stability and control augmentation systems for helicopter terrain flight [4IAA 82-1522] A82-38942 Modal control of relaxed static stability aircraft [AIAA 82-1524] A82-38944 An X-Hing aircraft control system concept [AIAA 82-1540] A82-38954 An alternate method of specifying tandfidth for flying gualities [ (AIAA 82-1609] A82-38988 X-29A flight control system design experiences [AIAA 82-1538] 482-39003 Piloted simulator evaluation of a relaxed static stability fighter at high angle-of-attack [AIAA PAPER 82-1295] A82-39082 Development and flight test evaluation of a pitch stability augmentation system for a relaxed stability L-1011 [AIAA PAPER 82-1297] 482-39084 Dynamic stability of flexible forward swept wing aircraft [4IAA PAPER 82-1325] A82-39102 A ground-simulation investigation of helicopter decelerating instrument approaches A82-39118 Maneuver stability of a vehicle with a towed body [AIAA PAPEE 82-1347] A82-39119 Sensor stabilisation requirements of RPV's - A simulation study A82-39711 Aerodynamic aspects of aircraft dynamics at high angles of attack /AGABD lecture/ [AIAA PAPER 82-1363] 482-39836 AIBCHAFT STBOCTUBBS Composite use on helicopters 482-38222 'Listening1 systems to increase aircraft structural safety and reduce costs A82-39539 On the state of technology and trends in composite materials in the United States A82-39882 Tests of CFBP spar/rib models with corrugated web 482-39890 Evaluation of CFBP prototype structures for aircraft A82-39892 Developments en graphite/epoxy T-2 nose landing gear door A82-39893 Fabrication of CPHP prototype structure for aircraft horizontal tail leading edge slat rail A82-39896 On the bearing strengths of CFBP laminates A82-39930 In-motion radiography of titanium spar tube welds A82-40538 Results of the AH-64 Structural Demonstration A82-40551 HAJIF-II - A program system for the dynaoic analysis of aeronautical structures 482-40884 Design of compensated flutter suppression systems A82-40904 The behavior of composite thin-walled structures in dynamic buckling under impact 482-40976 Nondestructive testing in aircraft construction using holographic methods 482-40977 Determination of load spectra and their application for keeping the operational life proof of sporting airplanes 482-41010 Theoretical and experimental investigation of joint-structural damping interaction for airplane construction 482-41013 Principles of achieving damage tolerance with flexible maintenance programs for new and aging aircraft 482-41016 Fatigue behavior of weldbonded joints A82-41115 Evaluation of heat damage to aluminum aircraft structures A82-41141 Advanced casting: loday and tomorrow aerospace industry components casting N82-28186 Nearfield aerodynamics and optical propagation characteristics of a large-scale turret model [AB-A113910] 882-28624 AIBCBAFT SOBVIVABILITY The correlation of flight test and analytic H-on-S air combat exchange ratios Many-on-Hany [AIAA PAPER 82-1328] 482-39105 AIBCBAFT TIBES Touchdown technology large aircraft lauding gear stress 482-40057 Alert aircraft roll over chocks [AD-A1C7456] B82-28307 AIBFOIL PBOFILES A new Transonic Airfoil Design Method and its application to helicopter rotor airfoil design A82-40507 Viscous transonic airfoil flow simulation A82-40897 Investigation of the unsteady airloads on a transport aircraft type airfoil with two interchangeable oscillating trailing edge flaps, at transonic speed and high Reynolds numbers 482-40909 Design and tests of airfoils for sailplanes with an application to the ASH-19B A82-40967 Variable geometry aerofoils as applied to the Beatty B-5 and B-6 sailplanes A82-40968 i-9 AIBFOILS SUBJECT IHDEX Advanced aerodynamic wing design for ccmmercial transports - Beview of a technology program in the Netherlands A82-409E5 Recent airfoil develcpaents at DFVLB 482-40986 1IHFOILS Observations and implications of natural laminar flow on practical airplane surfaces A82-40893 ilEFBiBE BAXEBIALS Sikorsky AC4P preliminary design Advanced Composite Airfraie Program A82-40526 AIHFBAMES A summary of weight savings data for composite VSTOL structure A82-40546 Inlet and airframe compatibility for a V/STOL fighter/attack aircraft kith top-mcunted inlets 482-40908 AIELISE OPERATIONS Complete flexibility and realism in radar simulation A82-38461 Fuel conservation: The airline - A1C A82-38464 Minimization of the total costs incurred in the employment of passenger jet aircraft A82-39247 The fourth dimension flight management system for airline operations A82-39540 FAA aviation forecasts-fiscal years 1982-1993 [AD-A114696] N82-29261 AIBPOBT PLAHKIHG Noise pollution and airport regulation A82-"0051 O'Hare International Airpcrt - Impervious to proposed state efforts to limit airport noise A82-40052 AIBPOBTS Computer outages at air terminal facilities and their correlation to near miss mid-air collisions (AFHD-82-43) [B-206064] N82-28264 FAA aviation forecasts-fiscal years 1982-1993 [AD-A114696] S82-29261 AIBSHIPS The feasibility of a high-altitude aircraft platform with consideration of technological and societal constraints [NASA-TH-84508] H82-29313 ALGOBITHHS A terrain following systen, an algorithm and a sensor A82-39740 Establishment of a rotor model basis [NAS4-TP-2026] N82-29311 ALIG1HEHT Hinimal order time sharing filters for INS in-flight alignment 482-38439 ALL-IBATHEB AIB 8A?IGATIOi Short range tactical Eld sjsten A82-39730 ALPHA JET AIBCBAFJ A one-shot autoclave manufacturing process for carbon epozy components A82-40935 ALTITODB COME01 Beduction and analysis of mode C altitude data collected at high altitudes over the continental United States [AD-A114655] B82-29276 ALOHINOB Fatigue behavior of weldbcnded joints A82-41115 ALOHINDH ALLOTS Material and process developments on the Boeing 767 482-10902 Application of a new hybrid material /ABALL/ in aircraft structures A82-40975 Evaluation of heat damage to aluminum aircraft structures A82-41141 Advanced casting: Today and tomorrow aerospace industry components casting N82-28486 ANALOG COBPOTEBS The use of analog computers in solutions of inverse problems of heat conduction for the identification of boundary conditions on the surfaces of gas-turbine-engine parts on the basis of temperature-measurement results A82-39467 ANALOG TO DIGITAL COHVEETBBS Heads up display [NASA-CASE-LAB-12630-1] H82-29319 ANGLE OF ATTACK Piloted simulator evaluation of a relaxed static stability fighter at high angle-of-attack [AIA4 PAPEB 82-1295] 482-39082 An estimation of aerodynamic forces and moments on an airplane model under steady state spin conditions [AIAA PAPEB 82-1311] A82-39092 Analysis and wind tunnel tests of a probe used to sense altitude through measurement of static pressure [AIAA P4PEB 82-1361] A82-39128 Effects of vortex breakdown on longitudinal and lateral-directional aerodynamics of slender vings by the suction analogy [AIAA PAPEB 82-1385] A82-39141 Lateral aerodynamics of delta wings with leading edge separation [AIAA PAPEB 82-1386] 482-39142 Aerodynamic aspects of aircraft dynamics at high angles of attack /AGABD Lecture/ [4144 P4PEB 82-1363] 482-39836 Flight-determined correction terms for angle of attack and sideslip [4144 SAPEB 82-1374] A82-40290 Dynamic surface measurements on a model helicopter rotor during blade slap at high angles of attack A82-40555 Determination of airplane aerodynamic parameters from flight data at high angles of attack A82-40928 Prediction of high alpha flight characteristics utilizing rotary balance data 482-40953 Lou-speed characteristics of a fighter-type configuration at high angles-of-attack and sideslip A82-41020 ABGLES (GBOHBTBY) Turbulent boundary layer on a porous surface with injection at various angles to the wall 482-39482 ABGOLAB ACCELBBAIIOH The ideal controlled element for real airplanes is not K/s [AIAA 82-1606] 482-38986 ANTES8A DESIGI Improved 243 MHz homing antenna system for use on helicopters [NLB-HP-81022-0] N82-28276 AHTESHA BADIATIOI PATTEBSS Honopole antenna patterns on finite size composite ground planes in aircraft A82-41055 AHTIHISTIBG FOELS Aviation fuels-future outlook and impact on aircraft fire threat H82-29282 APPB01CH CONTBOL In-Flight investigation of large airplane flying qualities for approach and landing [AIAA PAPEB 82-1296] A82-39083 An MIS with computer aided landing approach IAIAA PAPEB 82-1352] A82-39122 Instrument landing systeos /ILS/ at airports of the German Democratic Bepublic A82-39248 Terminal area automatic navigation, guidance, and control research using the Microwave Lauding System (MLS). Part 4: Transition path reconstruction along a straight line path containing a glideslope change waypoint [HASA-CB-3574-PT-4] H82-28269 Effects of approach lighting and variation in visible runway length on perception of approach angle in simulated night landings [AD-A114742] N82-29290 A-10 SUBJECT IBDBX AVIOBICS ABBA HAVIGATIOH HASA/FAA Helicopter ATC simulation investigation of BNAV/H1S instrumeat approaches A82-40535 ARBBD FOECES (OHITED STATES) N U.S. Harine Corps AV-SA maintenance experience [AIAA PAPEE 81-2657] A82-38446 ASTBPTOTIC BEIHODS Evaluation of an asymptotic fflethod fcr helicopter rotor airloads A82-40509 ATBOSPHEHIC CHEHISIBY Atmospheric chemistry of hydrocarbon fuels. Volume 2: Outdoor chamber data tabulations. Part 1 [AD-A113665] H82-28842 ATBOSPHEBIC COMPOSITION Two-dimensional model studies of the impact of aircraft exhaust emissions on trcpospheric ozone A82-40124 AIHOSPHEB1C DBHSIII Prelaunch estimates of near Garth satellite lifetimes using quasi-dynamic atmosphere models - application to a proposed Brazilian satellite[IHPE-2325-PBE/080] S82-29347 ATBOSPHERIC ELECTRICITY Atmospheric electricity hazards analytical model development and application. Volume 1: lightning environment modeling [AD-A114015] N82-29800 Atmospheric electricity hazards analytical model development and application. Volune 2; Simulation of the lightning/aircraft interaction event [AD-A114016] N82-29801 Atmospheric electricity hazards analytical model development and application. Volume 3: Electromagnetic coupling modeling of the lightning/aircraft interaction event[AD-A114017] N82-29802 ATBOSPHEHIC MODELS Two-dimensional model studies of the impact of aircraft exhaust emissions on tropcspheric ozone A82-10124 ATBOSPHEBIC IDBBOLEHCE The effects of atmospheric turbulence on a quadrotor heavy lift airship tAIAA 82-1542] A82-39009 The role of the scale parameter in service load assessment and simulation of aircraft flight A82-41011 The determination of gust loads on nonlinear aircraft using a power spectral density approach[HLB-TR-80 123-0] B82-28303 Analysis of vibration induced error in turbulence velocity measurements f rom an aircraft wing tip boom [NASA-CB-3571] S82-28881 ATTACK AIBCBAFT Mirage 2000 - Towards possible hiqh series production aircraft A82-38249 Inlet and airframe compatibility for a V/STOL fighter/attack aircraft nith top-mounted inlets A82-40908 Advanced aircraft electrical system control technology demonstrator. Phase 1: Analysis and preliminary design [AD-A113633] H82-28284 ADTOCUVIB6 A one-shot autoclave manufacturing process for carbon epoxy components A82-40935 AUTOMATIC COHIBOL Concept demonstration of automatic subsystem parameter monitoring military helicopter cockpit instrumentation A82-40530 AUTOBATIC FLIGHT COHIBOL PHCS - A commercial flijht management computer system [AIAA 82-1515] A82-38938 The use of differential pressure feedback in an automatic flight control system [AIAA 82-1596] A82-38981 Avoiding the pitfalls in automatic landing control system design [AIAA 82-1599] A82-39013 Primary-data devices Russian book Flight management computers Electronic stabilization of an aircraft A82-39279 A82-39321 A82-39322 The fourth dimension flight management system for airline operations A82-39540 A terrain following system, an algorithm and a sensor A82-39740 Flight control systems for aerial targets A82-39745 Boeing's new 767 eases crew workload A82-40348 Flight experience with a backup flight-control system for the HiHAT research vehicle[AIAi EAPEB 82-1541] A82-40429 A concept for 4D-guidance of transport aircraft in the IMA Terminal Haueuvering Area A82-40912 Seduced nonlinear flight dynamic model of elastic structure aircraft A82-41009 Investigations concerned with shifting pilot activities to a higher hierarchical stage of flight control German thesis A82-41453 Minimum operational performance standards for automatic direction finding (ADF) equipment [BTCA/DO-179] K82-28270 Applications to aeronautics of the theory of transformations of nonlinear systems [NASA-TM-84249] N82-30013 ADTOBATIC LABDIHG COSTHOL Avoiding the pitfalls in automatic landing control system design [AIAA 82-1599] A82-39013 An KLS with computer aided landing approach [AIAA EAPEB 82-1352] A82-39122 Terminal area automatic navigation, guidance, and control research using the Microwave Landing System (MLS). Part 4: Transition path reconstruction along a straight line path containing a glideslope change waypoint [NASA-CR-3574-PT-4] N82-28269 ADTOMATIC PILOTS Electronic stabilization of an aircraft A82-39322 The control and guidance unit for BACHAN A82-39738 Design and flight testing of a digital optimal control general aviation autopilot A82-40906 Gust response of commercial jet aircraft including effects of autopilot operation [NASA-CB-165919] N82-28266 ADTOMATIC TEST EQDIPBEHT A simple, lov cost application of a flight test parameter identification system [AIAA PAPEB 82-1312] A82-39093 ADTOBATIC TRAFFIC ADVISOEI ADD BESOLDTIOB Estimation of the number of in-flight aircraft on instrument flight rules A82-41117 AOTOBOTATIOB An evaluation of helicopter autorotation assist concepts A82-40524 AOIILIABI POiEB SOOECES An evaluation of helicopter autorotation assist concepts A82-40524 AVIONICS A preliminary laboratory evaluation of a reconfigurable integrated flight control concept [AIAA 82-1597] A82-38982 BACHAN - A unmanned aircraft flight research facility A82-39735 Future helicopter cockpit design A82-40529 Bicro-heads-up display A82-40533 Avionics systems for helicopter integration A82-40534 A-11 AXIAL FLO! TOBBIHBS SUBJECT IIDBI Support of the HH-65A - Tie lopact of advanced technology of VIOL systems upon existing product support A82~40541 A practical approach to tie incorporation of technical advances in avionics 482-40886 Preliminary design of an advanced integrated power and avionics infer nation system £82-40907 Models for the motor state of VSCF aircraft electrical power system Variable Speed Constant Frequency A82-40982 Electronic/electric technology benefits study —- avionics [BASA-CH-I65890] 882-28243 General aviation activity and avionics survey [AD-4112924] B82-28244 Advanced aircraft electrical system control technology demonstrator. Phase 1: Analysis and preliminary design [AD-A113633J 882-28284 Problems related to the integration of fault tolerant aircraft electronic systems £BASA-CB-165926] B82-29022 System data communication structures for active-contrcl transport aircraft, volume 2 [BASA-CB-165773-VOL-2J H82-29511 AXIAL FLOi XOBBIHBS Aerodynamics of advanced axial-flow turbomachinery [AD-A114911] 882-29328 B BEACOS COLLISIOH AVOItiHCB SISIEfl Air-air collision avoidance systeos A82-39323 BEABIB6LESS EOIOBS An experimental investigation of a bearingless model rotor in hcver A32-40512 Finite element analysis fox bearingless rotor blade aeroelasticity A82-40517 BBABIHGS Comparison of HP turbine 'deep blade design1 effects in turbofan engine gas generators with different bearing structure configurations A82-40996 BLADE SLIP BOISE The prediction of helicopter rotor discrete frequency noise A82-U0553 A semiempirical high-speed rotor noise prediction technique A 82-4 05 54 Dynamic surface measurements on a model helicopter rotor during blade slap at high angles of attack A82-40555 Helicopter model scale results of Hade-vortex interaction impulsive ncise as affected by blade planform A82-40556 BLADE TIPS Effect of tip vanes on the performance and flow field of a rotor in novel A82-40511 Investigation of a lotor system incorporating a constant lift tip [BASA-CB-166261] B82-29271 Multistage axial compressor program en tip clearance effects £40-4107445] 1182-29325 BLOHIBG Development cf an advanced no-moving-parts high-lift airfoil A82-40971 King-tip jets aerodynaxic performance A82-40987 BODIES OF BEVOLQIIOB Aerodynamic interactions between a 1/6-scale helicopter rotor and a body of revolution A82-40947 Aerodynamic interactions between a 1/6 scale helicopter rotor and a body of revolution [S4S4-TM-84247] H82-28252 BODT-II8G COHFIGDBAIIOHS An estimation of aerodynamic forces and moments on an airplane model under steady state spin conditions [AIAA PAPEB 82-1311] A82-39092 Bnnerical solution of a problem concerning transonic flow past a ving-fuselage configuration A82-39996 Transonic small disturbance code for body-King configuration coupled with full potential code for wing alone 482-40899 Computational and experimental studies of light twin aerodynamic interference A82-40930 Test results cf chordvise and spanwise blowing for low-speed lift augmentation A82-40999 lind tunnel test and aerodynamic analysis of three aeroelastically tailored wings A82-41001 Hind-tunnel investigation of vortex flaps on a highly swept interceptor configuration 482-41004 Hind tunnel measurements of longitudinal stability and control characteristics of primary and secondary wing configurations A82-41025 Means for controlling aerodynamically induced twist [HASA-CASE-IAB-12175-1 ] JJ82-28279 Besearch model wing/tail fabrication transonic wind tunnel 1/7.5-scale model [AD-A114101] B82-28288 BOEIBG AIBCBAFX Becent advances in rotor technology at Boeing Vertol A82-40508 Aerodynamic research applications at Boeing A82-41000 BOBIB6 747 AIBCBAFX B747/JT9D flight loads and their effect on engine running clearances and performance deterioration; BCAC BAIL/E and V.A JI9D engine diagnostics programs [H4S4-CB-165573] B82-28296 BOEIBG 767 AIBCBAFT Committing composites to the Boeing 767 A82-38224 Boeing's new 767 eases crew workload A82-40348 Material and process developments on the Boeing 767 A82-40902 BOHB1I AIBCBAFX Investigations regarding vortex formation at Kings with bent leading edges 482-38783 BOOBS (EQOIBBBBX) Analysis of vibration induced error in turbulence velocity measurements from an aircraft wing tip boom [H4S4-CB-3571] B82-28881 BOOHD4BI LAIEB COBIBOL External aerodynamic design for a laminar flow control glove on a Lockheed Jetstar wing 482-40895 4 summary of V/STOL inlet analysis methods [HASA-TM-82885] N82-28249 BOUNDAS! LAIEB BQOAXIOBS Symposium on Flows with Separation, Stuttgart, Best Germany, Bovember 23-25, 1981, Beports A82-38781 BODBDAEI LAIEB FLOi Improved solutions to the Falkner-Skan boundary-layer equation A82-38283 Comparison of experimental and analytic performance for contoured endwall stators [AIAA PAPEB 82-1286] A82-40422 Estimation of simulation errors in the European Transonic Hind Tunnel /ETH/ 482-40950 Aerodynamics of advanced axial-flow turbomachinery [4D-A114911] B82-29328 BOOIDABI LAIEB SEPABAIIOB Leading edge separation at delta wings with curved leading edges in supersonic flow 482-38784 A-12 SUBJECT IBDBX CLODO PHYSICS BOUNDABI VALUE EBOBLBHS Numerical methods for solving boundary value problems for noncavitating and cavitating flow past wing profiles A82-38722 The use of analog computers in solutions of inverse problems of neat conduction for the identification of boundary conditions on the surfaces of gas-turbine-engine parts on the basis of temperature-measurement results A82-39467 BOCKLIHG The behavior of composite thin-walled structures in dynamic buckling under impact A82-40976 BIPASS BATIO Recent advances in the performance of high bypass ratio fans A82-40891 C-1A AIBCBAFT Development of the advanced composite ground spoiler for C-1 medium transport aircraft A82-398S5 C-130 AIBCBAFT Besults of T56 engine performance monitoring trial in Hercules aircraft, Ferruary - July 1977 [ABL-aECH-ENG-IECH-aEMO-409] 882-29322 C-140 AIBCBAFT External aerodynamic design for a laminar flow contrcl glove on a Lockheed Jetstar wing A82-40895 C-141 AIBCBAFT Delta electrical load analysis C-141E JACC/CP aircraft [AB-A113761] B82-28283 CAHADAIB AIBCBAFT Canadair rotary ving technology development A82-39731 CABABD C08FIGOBAJIOHS Close-coupled canard-wing vortex interaction and Beynolds stress acguisition [AIAA PAPEB 82-1368] A82-39132 Calculations of transonic steady state aeroelastic effects for a canard airplane A 82-4 08 82 Tail versus canard configuration - An aerodynamic comparison with regard to the suitability for future tactical combat aircraft A82-40901 Test results cf chcrdwise and spanwise bloving for low-speed lift augmentation 482-40999 Optimization of canard configurations - An integrated approach and cractical drag estimation method A82-41023 Hind-tunnel investigation of a full-scale canard-configured general aviation aircraft A82-41024 Hind tunnel measurements of longitudinal stability and control characteristics of primary and secondary wing configurations A82-41025 Minimum induced drag ox canard configurations A82-41116 CAIOPIES Method for refurbishing and processing parachutes [NASA-CASE-KSC-11042-1] H82-29330 CABTILEVEB BEADS Tests of CFKt spar/rib models with corrugated web A82-39890 CABBOH FIBEB BEIHFOBCED PLASTICS Tests of CFBP spar/rib models with corrugated web A82-39890 Evaluation of CFBP prototype structures for aircraft A82-39892 Fabrication of CFBP prototype structure for aircraft horizontal tail leading edge slat rail A82-39896 On the bearing strengtus cf CFBP laminates A82-39930 Operation V10F - Development of a ccoposite material wing A82-40934 A one-shot autoclave manufacturing process for carbon epoxy components A82-40935 Development of materials and manufacturing technology over the next 20 years: Composite materials [HBB-OD-341-82-0J N82-28365 CABBOB FIBBBS • Technical and economic comparison of carbon fiber tape and woven fabric applications A82-40993 Carbon fiber reinforced composite structures protected with metal surfaces against lightning strike damage [BBB-OD-340-82-0/E] M82-28364 CASTIHG International aviation (selected articles) £AD-A114422] M82-28245 Advanced casting: Today and tomorrow aerospace industry components casting S82-28486 CATHODE BAI TUBES The evolution of display formats for advanced fignters using multimode color CBT displays A82-40888 CAVITATIOI FlOi numerical methods for solving boundary value problems for noncavitating and cavitating flow past wing profiles A82-38722 Use of the cavitation tunnel at the Dutch Naval Experiment station (SSP), Hageningen for the determination of the acoustic source strength of •propeller cavitation [TPD-908-720] B82-29116 CENTBAL PBOCBSSIIG OBITS Programs for the transonic wind tunnel data processing installation. Part 8: Programs for processing data on the central site computer £AD-A112900] S82-28310 CHABGE COUPLED DEVICES Fixed pattern noise correction for staring arrays in guidance systems A82-39190 CHIHA (HAIHLA1D) v International aviation (selected articles) £AD-A114422] 1182-28245 CIBCOLATIOH COBTBOL AUFOILS Development of the Circulation Control Wing-Upper Surface Blowing powered-lift system for STOL aircraft A82-40969 Development of an advanced no-moving-parts high-lift airfoil A82-40971 Design integration of CCH/USB for a sea-based aircraft A82-40972 CIVIL AVIATION The need for a dedicated public service helicopter design A82-38422 The national dynamics 'observer* mini-BPV for tropical operation A82-39734 New technology for the next generation of commercial transports - Beal or imaginary A82-41007 General aviation activity and avionics survey £AD-A112924] N82-28244 Cost analysis of the discrete Address Beacon System for the low-performance general aviation aircraft community [AD-A112957] N82-28274 Baxiaizing South Carolina's aviation resources: Identifying potentially profitable commuter airline routes, volume 2 [PB82-139353] N82-29277 CLBABA1CES CF6 jet engine performance improvement: High pressure turbine active clearance control [NASA-CB-165556] B82-28297 Hultistage axial compressor program on tip clearance effects [AD-A107445] N82-29325 CLOUD PBISICS An evaluation of the fiosemonnt ice detector for cloud water content measurements fPB82-158833] N82-29321 A-13 CLDTIEB SDBJECT IHDEX CLDSTEB Demonstration of radar reflector detection and ground clutter suppressicn using airborne weather and mapping racial A82-40532 COAL GASIFICAUOB Laboratory-scale simulation of underground coal gasification: Experiment and theory [DE82-001063] 882-2847,0 COCKPIT SIHOLATOBS Applying advanced techaolcgy to flight station design A82-40887 COCKPITS Analysis of in-trail following dynamics of CDTI-eguipped aircraft Cockpit Displays of Traffic Information [AJAA PAPEB 82-1330] A82-39107 Boeing's new 767 eases cre¥ workload £82-40348 Conceptual design cf toe IHX integrated cockpit A82-40527 Future helicopter cockpit design A82-40529 Concept demonstration of automatic subsystem parameter monitoring military helicopter cockpit instrumentation A82-40530 The evolution of display formats for advanced fighters using multuiode color CBT displays A82-40888 Electronic/electric tecanclogy benefits study avionics [BASA-CR-165890] B82-28243 COLLISION AVOIDABCE * Air-air collision avoidance systems A82-39323 COLOB Aircraft geometry verification with enhanced computer generated displays [BASA-TH-84254] S82-29268 COLOHHS (SUPPOBIS) The behavior of composite thin-walled structures in dynamic buckling under impact A82-40976 COBBAI ' The correlation of flight test and analytic B-on-H air combat exchange ratios fiany-ou-Bany [iliA PAPEE 82-1328] A82-39105 COHBIBED SIBESS A crack growth model uader spectrun loading A82-40961 COHBDSTIOB Laboratory-scale simulatico of underground coal gasification: Experiment and theory [DE82-001063] 882-28470 COHflAHD AMD COBIBOL U.S. Army remotely piloted vehicle supporting technology program A82-39739 Flying qualities requirements for rcll CAS systems [AIAA PAPEE 32-1356] A82-40287 COMKEBCISL AIBCBAFT Progress at Douglas on laminar fio* control applied to commercial transport ^aircraft A82-40958 Aerodynamic research applications at Boeing A82-41000 Hew technology for the neit generation of commercial trans forts - seal or imaginary A82-41007 Gust response of commercial jet aircraft including effects of autcpilot operation fBASA-CB-165919] 882-28266 FAA aviation forecasts-fiscal years 1982-1993 £AD-A114696] • B82-29261 COHHEBCIAL E1EBGI Maximizing South Carolina's aviation resources: Identifying potentially profitable commuter airline routes, volume 2 [PB82-139353] H82-29277 COHHOHIC1IIHG Communications H82-29302 COHHDHICATIOH HETiOBKS System data communication structures for active-contrcl transport aircraft, volume 1 [NASA-CB-165773-VOL-1] N82-29510 System data communication structures for active-control transport aircraft, volume 2 [HASA-CH-165773-VOL-2] 882-29511 Electromagnetic Propagation Problems in the Tactical Environment fAGABD-LS-120] S 82-29527 COHB01HIES Field studies of the Air Force procedures (BOISECflECK) for measuring community noise exposure f rom aircraft operations [AD-A113672] 882-28841 COHPEBSATOBY TBACKI8G The effects of the delays on systems subject to manual control A82-38943 COBPOSEH1 BBLIiBILIM Reliability model for planetary gear {NASA-TB-82859] N82-28643 COHPOSITE BATBBIALS On the state of technology and trends in composite materials in the Dnited' States A82-39882 Fasteners for composite structures A82-39929 In-plane shear test of thin panels A82-40545 Application of composite materials and new design concepts for future transport aircraft A82-40994 Composite structures repair A82-41015 Eecent development in hygrothermoviscoelastic analysis of composites N82-28676 COHPOSI1E SIBOCfOBBS Composite use on helicopters A82-38222 Toward all-composite helicopter fuselage A82-38223 Committing composites to the Boeing 767 A82-38224 Calculation of the cross section properties and the shear stresses of composite rotor blades A82-38475 Design, fabrication and qualification of the T-2 composite rudder A82-39894 Sikorsky ACAP preliminary design Advanced Composite Airfraae Program A82-40526 Development of the Sea King composite main rotor blade A82-40539 Design and fabrication of a composite rear fuselage for the OH-60 /Black Hawk/ A82-40544 The behavior of composite thin-walled structures in dynamic buckling under impact A82-40976 Design and fabrication of cocared composite hat-stiffened panels A82-40978 Sliced disc design - A composite conform concept for a turbo engine axial compressor A82-40995 Bonopole antenna patterns on finite size composite ground planes in aircraft A82-41055 Bational Transonic Facility (HTF) prototype fan blade fatigue test [AD-A114405] • 882-28261 Carbon fiber reinforced composite structures protected with metal surfaces against lightning strike damage {UBB-OD-340-82-0/E] N82-28364 COHPBESSIBG Ethanol production by vapor compression distillation £DE82-004892] B82-29393 COBPBESSIOH LOADS Cracks interacting with contact forces - A finite element study on loaded boles A82-40959 COHPBESSOB BLADES Application of the sequential optimization method to the tuning of the natural frequencies of gas-turbine engine compressor blades A82-39399 A-14 SUBJECT IBDIX COHCBETES Sliced disc design - A coufosite conform concept for a turbo engine axial compressor A82-40995 B747/JI9D flight loads and their effect on engine running clearances aad performance deterioration: BCAC BAIL/P and ii.i J19D engine diagnostics programs [NASA-CB-165573] N82-28296 COHPDTATIOiAL J10ID DIHIBICS Improved solutions to the Falkner-£kan boundary-layer eguation A82-38283 Numerical methods for solving boundary value problems fcr noncavitatang and cavatating flov past wing profiles A82-38722 Calculation cf level flow using radial grating A82-38922 Humerical solution of 3 problem concerning transonic flov past a wing-fuselage configuration A82-39996 Viscous transonic airfoil flow simulation A82-40897 Computation of supersonic flow around three-dimensional Kings 482-40898 Transonic snail disturbance code for body-King configuration coupled with full potential code for wing alcne 482-40899 A summary of V/ST01 inlet analysis methods 482-40921 Computational and experimental studies of light tvin aerodynamic interference 482-40930 An experimental and nunerical study of 3-D rotor wakes in hovering flight 482-40946 Estimation of simulation errors in the European Transonic Rind lunnel /BIB/ 482-40950 Analytical study of voctex flaps on highly swept delta wings A82-41003 Analysis of jet transport kings with deflected control surfaces by using a combination of 2- and 3-D methods 482-41022 A finite difxerence method for the calculation of transonic flow about a wing, based on small perturbation theory [NLB-TB-81031-0] N82-28263 iindtnnnel capability related to test sections, cryogenics, and computer-vindtunnel integration [AGABD-AB-174] N82-29334 COHPDTBB AIDED EESJGB Efficient optimum design of structures - Program DDDU 482-38146 Primary-data devices Russian book A82-39279 The application of snail propellers to BPV propulsion A82-39737 The use of linearized-aerodynamics and vortex-flow methods in aircraft Jesign /invited paper/ [4IAA PAPEE 82-1384] A82-40294 & new Transonic Airfoil Design flethod and its application to helicopter rotor airfoil design 482-40507 Optimum structural design for helicopters 482-40543 Engineering aspects'of international collaboration on Tornado 482-40878 CATIA - A computer aided design and manufacturing tridimensicnal systea 482-40990 CDS-the designer's media, the analyst's model Configuration Developaent System for aircraft 482-40991 Aircraft geometry verification with enhanced computer-generated displays 482-40992 Automated optimum desijn of wing structures. Deterministic and probabilistic approaches [NAS4-TH-84475] N82-29317 COSPCTEB AIDED flAHOFACIOBIBG Computer aided coordinate measuring systems in engineering design of helicopter components 482-40540 C4TIA - A computer aided design and manufacturing tridimensional system A82-40990 Aircraft geometry verification with enhanced computer-generated displays A82-40992 COMPUTES GB4PHICS Design and construction of a flexible autonomic electronic display device for flight control 482-40569 CA1IA - 4 computer aided design and manufacturing tridimensional system 482-40990 Aircraft geometry verification with enhanced computer-generated displays 482-40992 Aircraft geometry verification with enhanced computer generated displays [NAS4-1B-84254] B82-29268 coaeayES PBOGBABS HAJIF-II - A program system for the dynamic analysis of aeronautical structures 482-40884 Computer program for analysis of spherical screen distortion [AD-4113136] * U82-28309 Programs fcr the transonic wind tunnel data processing installation. Fart 8: Programs for processing data on the central site computer [AD-4112900] . N82-28310 Field studies of the Air Force procedures (MOISECHECK) for measuring community noise exposure from aircraft operations £40-4113672] S82-28841 Geophysical flight line flying and flight path recovery utilizing the Litton LTB-76 inertial navigation system [DE82-005555] S82-29292 Effect of water on axial flow compressors. Fart 2: Computational program [4D-4114.831] B82-29327 User's manual for the AMEEE flight path-trajectory simulation code [DE82-007004] S82-29343 COBPOTEB SISTEHS DESIGH Future terminal area systeas 482-38462 Problems related to the integration of fault tolerant aircraft electronic systems [»4S4-CE-165926] N82-29022 COHPDIEB TECHHIQOES Computer-aided derivation of equations of motion tor rotary-wing aeroelastic problems 482-40883 Computer program for analysis of spherical screen distortion [AD-4113136] N82-28309 COHPDIEBIZED SIBOLATIOS Problems in the simulation of correlation-extremal navigation systems 482-39403 Terrain following/terrain avoidance system concept development [4144 PAPEB 82-1518] 482-40428 Dynamic energy transfer between wind and aircraft 482-40939 Optimal open-loop aircraft control for go-around maneuvers under wind shear influence 482-40943 Inflight 1FB procedures simulator [N4S4-CASE-KSC-11218-1] N82-29331 User's manual for the JBEEE flight path-trajectory simulation code [DE82-007004] N82-29343 COHPOTEBS Computer outages at air terminal facilities and their correlation to near miss mid-air collisions (AFHD-82-43) £i-206064] K82-28264 Aerodynamics cf advanced axial-flow turbomachinery [AD-4114911] N82-29328 COSCBEIES Hater-compatible polymer concrete materials for use in rapid repair systems for airport runways [DE82-010994] N82-29464 4-15 COHFEBEICES SUBJECT IIDBX COBFEBEHCES Symposium on Pious vita Separation, Stuttgart, West Germany, November 23-25, 1961, Beports A82-38781 Bemotely piloted vehicles; International Conference, 2nd, Bristol, England, April 6-8, 1981, Conference Papers and Supplementary Papers 482-39727 American Helicopter Society, Annual Forum, 38th, Anaheim, CA, Hay 4-7, 1S£2, Proceedings 182-40505 International Council of tie Aeronautical Sciences, Congress, 13th and AIAA Aircraft Systems and technology Conference, Seattle, WA, August 22-27, 1S82, froceedings. Volumes 11 6 2 A82-40876 CONICAL BODIES Summary of sting interference effects for cone, missile, and aircraft configurations as determined by dynamic and static measurements [AI6A PAPEB 82-1366] A82-403S5 COHSOLES Controls N82-29301 COHSTBAIHTS Human capabilities and limitations in systems H82-292S7 COHTOUBS Comparison of experimental and analytic performance for contoured endvall stators [AIAA PAPEB 82-1286] A82-40422 COHTBOL BOABDS Controls H82-29301 COHTBOL COHFIGDBED VEHICLES Design and flight testing of digital direct side-force contrcl lavs [AIAA 82-1521] A82-38941 X-29A flight ccntrcl system design experiences [AIAA 82-1538] A82-39003 Design and analysis of a multivariable control system for a ccv-typa fighter aircraft [AIAA PAPEE 82-1350] A82-39121 Progress at Douglas on laminar flov control applied to commercial transport aircraft A82-40958 COHTBOL EQOIPHEHI Generic faults and design solutions for flight-critical systaiis [AIAA 82-1595] A82-38980 Primary-data devices Bossian book A82-39279 Flight experience vith a backup flight-control system for the HiHAT research vehicle [AIAA PAPEB 82-1541] A82-40429 Beans for controlling aerodynamically induced tvist [HASA-CASE-LAB-12175-1] H82-28279 CONTBOL SIHOLATIOS Piloted simulator evaluation of a relaxed static stability fighter at nigh angle-cf-attack [AIAA PAPEB 82-1295] A82-39082 Sensor stabilisation r acquirements cf BPT's - A simulation study A82-39741 The design of a BPV ground station simulator A82-39750 CONTBOL STABILITY Modal control of relaxed static stability aircraft [AIAA 82-1524] A82-38944 COHTBOL STICKS Simulator investigations cf various side-stick controller/stability and contrcl augmentation systems for helicoptar terrain flight [AIAA 82-1522] A82-38942 COHTBOL SDBFACES Tne use of differential pressure feedback in an automatic flight control system [AIAA 82-1596] A82-38981 Analysis of jet transport mngs vith deflected control surfaces by using a combination of 2- and 3-D methods A82-41022 COHTBOL THEOBI Application of multivariaile model following method to flight controller [AIAA PAPEfi 82-1349] A82-39120 A modern approach to pilot/vehicle analysis and the Meal-Siith criteria [AIAJ PAPEE 82-1357] A82-39125 Applications to aeronautics of the theory of transformations of nonlinear systems [NASA-TH-84249] H82-30013 COHTBOILABILITI Pilot models for discrete maneuvers [AIAA 82-1519] A82-38940 Smulator investigations of various side-stick controller/stability and control augmentation systems for helicopter terrain flight [AIAA 82-1522] A82-38942 Handling qualities criteria for flight path control of V/STOL aircraft [AIAA PAPEB 82-1292] A82-39081 In-Flight investigation of large airplane flying gualities for approach and landing [AIAA PAPEB 82-1296] A82-39083 Guidance for the use of equivalent systems vith HII-F-8785C for aircraft flight control systems [AIAA PAPEE 82-1355] 482-391.24 Flying gualities requirements for roll CAS systems [AIAA PAPEB 82-1356] A82-40287 Evaluations of helicopter instrument-flight handling gualities [AD-A114004] 882-28285 Analytical and simulator study of advanced transport [NASA-CB-3572] 082-28298 A discussion of the flying gnality requirements of a lasic training aircraft [AD-A114805] B82-29318 COHTBCLLEfiS Bedundant control unit for an advanced multispool engine A82-40998 COiVECTIfE HBAI HAHSFEB The use of analog computers in solutions of inverse problems of heat conduction for the identification of boundary conditions on the surfaces of gas-turbine-engine parts on the basis of temperature-measurement results A82-39467 COH?EBSATIOI Coamunications N82-29302 COITE10BS Bethod for refurbishing and processing parachutes [HASA-CASE-KSC-11042-1] 882-29330 COBBE1ATIOB DBTBCTIOB Target tracking using area correlation A82-39194 Simulation of correlation-extremal receivers of signals from sampling-phase radio-navigation systems A82-39404 COBBOfiATED PLATES Non-honeycomb F-16 horizontal stabilizer structural design A82-40936 COST AHALISIS Minimization of the total costs incurred in the employment of passenger jet aircraft A82-39247 Cost analysis of the discrete Address Beacon System for the low-performance general aviation aircraft community [AD-A112957] H82-28274 COST BBDOCTIOH 'listening' systems to increase aircraft structural safety and reduce costs A82-39539 Unmanned aircraft' in future combat A82-39728 Horses for courses in BPV operations system components design and development in terms of performance and cost A82-39729 Advanced technologies applied to reduce the operating costs of small comouter transport aircraft A82-40915 Technical and economic comparison of carbon fiber tape and voven fabric applications A82-40993 COTABIAICE Minimal order time sharing filters for INS in-flight alignment A82-38439 1-16 SUBJECT IHDBX DELTA BIBGS CHICK PBOPAGATIOH Cracks interacting vita contact forces - A finite element stud; on loaded boles A82-40959 A crack growth model under spectrum leading 482-40961 Prediction of fatigue crack growth rates under variable loading using a simple crack closure model [NLB-HP-81023-0] N82-28685 CEiSH 1HJOEIES Crashvorthiness studies: Cabin, seat, restraint, and injury findings in selected general aviation accidents [AD-A114878] N82-29275 CEASBES Crashvorthiness studies: Cabin, seat, restraint, and injury findings in selected general aviation accidents [AD-A114878] 1182-29275 Aircraft fire safety [AGABD-1S-123] N82-2S279 Aircraft fire mishap experience/crash fire scenario guantitation H82-29280 Human response to fire N82-29281 Fuel system protection methods H82-29283 CRASH10BIHIHESS Structural design of a crashworthy landing gear for the AH-64 Attack ilelicopter A82-40547 Crashvorthiness studies: Cabin, seat, restraint, and injury findings in selected .general aviation accidents [AD-A114878] M82-29275 Aircraft post crash fire reducticn/sorvivability enhancement from a manufacturer's viewpoint H82-29286 CHOP DUS1IHG Agricultural airplane aission time structure characteristics [NASA-IH-84470] 882-29329 CBOSS COOPLIBG The use of a multi-degree-cf-freedom dual balance system to measure cross and cross-coupling derivatives [AD-A114813] S82-29333 CRUDE OIL Aviation fuels-future outlcck and impact on aircraft fire threat N82-29282 CRIOGEUC HMD TOHHE1S Estimation of simulation errors in the European Transonic lind Tunnel /I1H/ 482-40950 Hindtunnel capability related to test sections, cryogenics, and computer-tindtunnel integration [AQABD-AB-174] H82-29334 GOES flanual reversion flight control system for A-10 aircraft: Pilot performance and simulator cue effects [AD-A113463] 882-28302 COBBEHT DISIBIBOIIOH Delta electrical load analysis C-141E JACC/CP aircraft fAI>-A113761] H82-28283 CXCLIC LOADS Prediction of fatigue crack growth rates under variable loading using a simple crack closure model [m.B-MP-81023-D] 1182-28685 DAH1GE 4SSESSBBHT Besearch on the behavior of a turbojet engine duting internal and external disturbances with respect to early recognition of damage German thesis A82-40561 Composite structures repair A82-41015 Principles of achieving callage tolerance with flexible maintenance programs for new and aging aircraft A82-41016 Evaluation of heat damage to aluoinum aircraft structures A82-41141 DATA ACQUISITION The detection o£ low level wina shear. II A82-38463 Advanced trending analysis/EDS data program [AD-A113511] N82-28286 Seduction and analysis of mode C altitude data collected at high altitudes over the continental United States [AD-A114655] , N82-29276 DATA BASE HAIAGEBBBT SYSTBHS Opto-electronical push-broom scanners for navigation, reconnaissance and generation of digital data bases A82-39747 DATA COBBELATIOB A recursive terrain height correlation system using multiple model estimation techniques [AIAA 82-1513] A82-38937 Investigation of correlation between full-scale and fifth-scale mnd tunnel tests of a Bell "helicopter Textron Model 222 (HASA-CB-166362] N82-29315 Correlation of Preston-tube data with laminar skin friction (Log So. J12984) [NASA-TH-84827] N82-29556 DATA LINKS Application of an optical data link in the airborne scanning system A82-39275 U.S. Aray remotely piloted vehicle supporting technology program A82-39739 DATA BAHAGEHEBT PHCS - A commercial flight management computer system [AIAA 82-1515] A82-38938 DATA PBOCESSIBG Primary-data devices Russian book A82-39279 Hydraulic Universal Display Processor System (HODPS) [AD-A114428] N82-28294 Programs for the transonic wind tunnel data processing installation. Part 8: Programs for processing data on the central site computer [AD-A112900] N82-28310 DATA PBOCESSIHG 1EBHIIALS Terminal inforaation display system benefits and costs [AE-A114937] N82-29291 DATA BEDDCTIOB Seduction and analysis of mode C altitude data collected at high altitudes over the continental United States [AD-A1146S5] S82-29276 DATA TBAHSBISSIOH System data communication structures for active-control transport aircraft, volume 1 [NASA-CB-165773-VOL-1] N82-29510 System data communication structures for active-control transport aircraft, volume 2 [BASA-Ca-165773-70L-2] S82-29511 Propagation problems associated with aircraft communications systems N82-29535 DEAD BECKOHIHG The control and guidance unit for HACHAN A82-39738 DEGBEES OP PBEEDCd Use of rotary balance and forced oscillation test data in six degrees of freedom simulation [AIAA PAPE.B 82-1364] A82-39129 The use of a multi-degree-of-freedom dual balance system to measure cross and cross-coupling derivatives [AD-A114813] S82-29333 DEICEBS An evaluation of the Bosemount ice detector for cloud water content measurements [PB82-158833] H82-29321 DELIA 8IBGS Leading edge separation at delta wings with curved leading edges in supersonic flow 482-38784 Measurement and visualization of skin friction on the leeside of delta vings in supersonic flow 482-38785 A-17 DESIGN 4SALISIS SOBJECT IHDEI Measurements of velocity distributions in the leading edge vortex of. a delta wing by the laser-Soppier procedure A82-387£6 Dynamic load measurements with delta wings undergoing self-induced roll-oscillations [AIAA PAPEB 82-1320] A82-39098 Lateral aerodynamics of delta wings with leading edge separation [AIAA PAPEI 82-1386] A82-39142 Vortex formation over Jouble-delta wings A82-40989 Upper Vortex Flap - A versatile surface for highly swept wings A82-41002 Analytical study of vortex flaps on highly swept delta wings A82-41003 Spanwise distribution of vortex drag and leading-edge suctioa in subsonic flow A82-41005 Fuselage effects in leading edge vortex flap aerodynamics A82-41006 DESIGN ANALYSIS A design criterion for highly augmented fly-by-wire aircraft [AIAA 82-1570] A82-38969 Avoiding toe pitfalls in automatic landing control system design [AIAA 82-1599] A82-39013 Development of the advanced composite ground spoiler for C-1 medium transport aircraft A82-39895 Analytical design and validation of digital flight control system structure[AIAA PA?E£ 82-U26] A82-40434 CDS-the designer's media, the analyst's model Configuration Development System for aircraft A82-40991 The determination of gust loads on nonlinear aircraft using a powar spectral density approach[HLB-TB-80123-U] H82-28303 Design basis for a new transonic wind tunnel [AD-A112899] 882-28311 Advanced casting: Today and tomorrow aerospace industry ccm[ clients casting N 82-28 4 86 Problems related to the integration cf fault tolerant aircraft electronic systems [NASA-CB-165926] N82-29022 DESIGB TO COST The promise cf laminated metals in aircraft design A82-U0903 Design and experience with a low-cost digital fly-by-wire system ia the SAAB JA37 Viggen A/C A82-40905 Optimizing aerospace structures for manufacturing cost A82-41014 DIFFBBENTIAL PBESSDBB The use of differential pressure feedback in an automatic flight control system [AIAA 82-1596] A82-38981 DIGITAL COBHAHD SISTBHS Design and flight testing cf digital direct side-force contrcl laws [AIAA 82-1521] A82-38941 DIGITAL DATA Heads up display [HASA-CASE-1AB-12630-1 ] N82-29319 DIGITAL PILTBBS Hinimal order time sharing filters fcr INS in-flight alignment A82-38439 DIGITAL NAVIGATION PNCS - A commercial flight management coaputer system [AIAA 82-1515] A82-38938 The Shiryayev seguential probability ratio test for redundancy manageoent [AIAA 82-1623] A82-38998 Problems in the simulation of correlation-extremal navigation systems A82-39403 Simulation of correlation-extremal receivers of signals frcm sanclinj-phase radio-navigation systems A82-39404 The control and guidance unit for HACUAN A82-39738 DIGITAL BADAB SYSTEHS Badars for DHfi A82-39742 DIGITAL SIHOLATICN Digital computer simulation of modern aeronautical digital communication systems A82-40940 DIGITAL SISXEflS Analytical design and validation of digital flight contrcl system structure [AIAA PAPEB 82-1626] A82-40434 Advanced fighter technology integration program AFTI/J-16 A82-40900 Design and experience with a low-cost digital fly-by-wire system in the SAAB J437 Viggen A/C A82-40905 Design and flight testing of a digital optimal control general aviation autopilot A82-40906 Bedundant control unit for an advanced multispool engine 482-40998 DIGITAL TECHNIQUES Digital full authority controls for helicopter engines A82-40522 DIBECT LIFT COHIBOLS Design and analysis of a mnltivariable control system for a ccv-type fighter aircraft [AIAA PAPEB 82-1350] A82-39121 DISCBBTE ADDBESS BEACON SISIBH Cost analysis of the discrete Address Beacon System for the low-performance general aviation aircraft community [AD-A112957] N82-28274 DISPLAY DEVICES The detection of low level wind shear. II A82-38463 Analysis of in-trail following dynamics of CDTI-eguipped aircraft Cockpit Displays of Traffic Information [AIAA PAEEB 82-1330] A82-39107 Conceptual design of the LHX integrated cockpit A82-40527 Future helicopter cockpit design A82-40529 Evaluation of an automatic subsystem parameter monitor for aircraft A82-40552 Design and construction of a flexible autonomic electronic display device for flight control 482-40569 The evolution of display formats for advanced fighters using multimode color CBT displays 482-40888 Visual scene simulation concerning the landing of sporting aircraft in connection with investigations regarding the control and learning behavior of the pilot German thesis A82-41447 Electronic/electric technology benefits study avionics [HASA-CB-165890] H82-28243 Hydraulic Universal Display Processor System (HODPS)[AD-A114428] N82-28294 Coaputer program for analysis of spherical screen distortion [AD-A113136] N82-28309 Terminal information display system benefits and costs [AD-A114937] H82-29291 Displays B82-29300 DISTILLATION Ethanol production by vapor compression distillation[DE82-004892] N82-29393 DOHES (STBOCTOBAL FOBHS) Nearfield aerodynamics and optical propagation characteristics of a large-scale turret model[AD-A113910] H82-28624 DOOBS Developments en graphite/epoxy T-2 nose landing gear door 482-39893 A-18 SUBJECT IIDBI BHOTIOHAL PACTOBS DEAG BBDOCIIOB Development and flight test evaluation of a pitch stability augmentation sjstem for a relaxed stability 1-1011 [AIAA PAPEE 82-1297] 482-39084 The use ot snail strakes tc reduce interference drag of a Ion wing, twin engine airplane [AI14 PAPEB 82-1323] A82-39100 NASA research on viscous drag reduction 482-40896 Optimization of canard configurations - An integrated approach and practical drag estimation nethod 482-11023 Binimum induced drag ox canard configurations 482-11116 DBOP 1ESIS Structural design of a crashworthy landing gear for the AH-64 Attack Helicopter 482-40547 COAL II86 COBFI6UBATI01S Dual wing, swept forKara swept rearward Ming, and single ving design optiiization for high performance business airplanes 482-40931 DIBABIC CHAHACTIBISHCS Flap-lag-torsional dynamics of exten£ional and inextensional rotot olades in hover and in forward flight [HASA-Cfi-169159] 882-29312 DIBAMIC HODEIS Determination of airplaae eerodynaeic paraneters from flight data at aigh angles cf attack 482-40928 Beduced nonlinear flignt dynamic model of elastic structure aircraft 482-41009 DISABIC BESPOHSE Dynamic energy transfer between Hind and aircraft 482-40939 Limiting performance of nonlinear systems with applications to helicopter vibraticn control problems [4D-A113239] 882-28301 DI14HIC STABILITY Analyzing stable pad disturbances and design of a sensor vault to monitor tad stability [AIAA 82-1565] 482-39011 Dynamic stability of flexible forward suept ving aircraft [AIAA P4PEE 82-1325] 482-39102 Maneuver stability of a vehicle with a towed body [4144 P4PEB 82-1347] 482-39119 DTHABIC SIBOCTOBAL AHALISIS Whirl mode stability o£ the main rotor of the Y4H-64 Advanced Attack helicopter A82-40513 HAJIF-II - A program systea for the dynamic analysis of aeronautical structures 482-40864 Theoretical and expeciaental investigation ofjoint-structural damping interaction for airplane construction 482-41013 DIHABIC TESTS Dynamic load measurements with delta wings undergoing self-induced roll-oscillations [ A I A A PAPEB 82-1320] 482-39098 Analytic extrapolation to full scale aircraft dynamics [AI4A PAPE.B 82-1387] 482-39143 EABTfl TEBHIHALS O.S. Army remotely piloted vehicle supporting technology program 482-39739 ECOBOBIC AiALISIS Historical research and development inflation indices for Amy fixed and rotor winged aircraft [AD-A114368] 882-28290 EJECTIO1 SEATS Comparative vertical inpact testing of the F/FB-111 crew restraint system and a proposed modification £40-4113957] H82-28267 EJECTOBS Ejector powered propulsion and high lift subsonic wing 482-40970 ELASTIC BODIES Beduced nonlinear flight dynamic model of elastic structure aircraft A82-41009 E1ASIODXH1HICS The effect of hybrid composite materials on the dynamic characteristics of helicopter rotor blades A82-3926J ELECTBIC POIBB SUPPLIES Preliminary design of an advanced integrated power and avionics information system 482-40907 Models for the motor state of VSCF aircraft electrical power system Variable Speed Constant Frequency A82-40982 Delta electrical load analysis C-141B J4CC/CE aircraft [4D-A113761] 882-28283 ELECTBIC POiEB TEABSHISSIOB Feasibility study of a 270V dc flat cable aircraft electrical power distributed system [AD-A114026] 882-28552 System data communication structures for active-control transport aircraft, volume 1 [BAS4-CB-165773-VOL-1] M82-29510 ELECTBIC PBOPDLSIOH Electric propulsion for a mini BPV system 482-39744 ELECTBO-OPTICAL PHOTOGRAPH! Target tracking using area correlation A82-39194 ELECTBCHAGHETIC FIELDS Atmospheric electricity hazards analytical model development and application. Volume 3: Electromagnetic coupling modeling of the lightning/aircraft interaction event [AD-A114017] 882-29802 BLECTBOBAGBETIC PBOPEBTIES Atmospheric electricity hazards analytical model development and application. Volume 1: Lightning environment modeling [4D-4114015] H82-29800 ELECTBOHAGSETIC iAVB TBANSBISSIOH Electromagnetic Propagation Problems in the Tactical Environment [4G4BD-LS-120] N82-29527 Propagation problems associated with aircraft communications systems 882-29535 ELECTBOBIC COiTBCL Electronic stabilization of an aircraft 482-39322 Adaptive fuel control feasibility investigation 482-40519 Digital full authority controls for helicopter engines 482-40522 Engine controls for the 1980s and 1990s 482-40984 ELECTEDHIC EQOIEHEBT Future helicopter cockpit design 482-40529 Design and construction of a flexible autonomic electronic display device for flight control 482-40569 A compendium of lightning effects on fu ture aircraft electronic systems [AD-4114117] 882-28293 ELEVOBS Methodology for determining elevon deflections to trim and maneuver the DAST vehicle with negative static margin f84S4-TH-84499] 882-28299 EHBEDDIBG On embedded flow characteristics of sharp edged rectangular wings [LCG-C4712] 882-29263 EHEBGEHCIES An evaluation of helicopter autorotation assist concepts 482-40524 EBOTI084L FACTOBS Aircraft fire safety [AGAfiD-LS-123] 882-29279 A-19 EHBBSY COHSEBVATICN SUBJECT INDEX ENEBGX COHSEBVATIOB Fuel conservation: The airline - AIC 282-38464 Third generation turbo fans A82-40964 EHEBGI BEQOIBEBEHJS Beguirements and trends in fuel consumption in transport mission with aircraft and sarface vehicles A82-40956 ENBBGI TEABSFBB Dynamic energy transfer betteen wind and aircraft A82-40939 ENGINE AIBFBABE INTEGBATION Evaluation of an experimental technique to investigate the effects cf the engine position on engine/pylon/wing interference wind tunnel tests [HLE-HP- 81020-0] H82-28262 EHGIBE COBIBOL Optimal control application in supersonic aircraft performance A82-39374 Application cf the sequential optimization method to the tuning of the natural frequencies of gas-turbine engine compressor blades A82-39399 Digital full authority controls for helicopter engines A82-40522 Engine controls for tha 1S£Gs and 1990s A82-40984 Bedundant control unit for an advanced multispool • engine A82-40998 ENGINE DESIGH Propulsion opportunities for future commuter aircraft [ilAA PAPEE 82-1049] A82-40418 800 Shaft Horsepower Advanced Technology Demonstrator Engine A82-40520 TF34 Convertible Engine System Technology Program A82-40521 Optimized 10 ton class commercial aircraft engine A82-40890 Secent advances in the performance of high bypass ratio fans A82-40891 Third generation turbo fans A82-40964 Sliced disc design - A composite conform concept for a turbc engine axial compressor 482-40995 Comparison of HP turbins 'deep blade design1 effects in turbofan engine gas generators with different bearing structure configurations A82-40996 QCSEE over-the-wing enjine acoustic data [NASA-TH-82708] H82-29324 ENGINE PAILOBE Electronic stabilization of an aircraft . A82-39322 Besults of 156 engine performance monitoring trial in Hercules aircraft, February - July 1977 [ARL-HECH-ENG-TECH-at,10-l|09] H82- 29322 EHGIBE INLETS Forward velocity effects en fan noise and the suppression characteristics of advanced inlets as measured in the NASA-Ames 40 by 80 foot wind • tunnel [NASA-CB-152328] -K82-30030 ENGIHE BCNITOBIBG IHSIBOflBHIS Civil helicopter propulsic.1 system reliability and engine monitoring technclogy assessments A8 2-40518 Besearch on the behavior of a turbojet engine during internal and external disturbances with respect to early recognition of damage German thesis A82-40561 ENGIHE NOISE Static noise tests en modified augmentor wing jet STOI research aircraft £SASA-TI1-81231 ] BS2-282S5 QCSEE over-the-wing enjj.no acoustic data [HASA-TH-82708] B82-29324 Estimated airplane noise levels in A-veighed decibels [AC-36-3B] M82-30029 Forward velocity effects on fan noise and the suppression characteristics of advanced inlets as measured in the NASA-Ames 40 by 80 foot vind tunnel [H1SA-CB-152328] S82-30030 Far-field acoustic data for the Texas ASE, Inc. hush house [AD-A114564] H82-30032 ENGIHE PABTS Propulsion opportunities for future commuter aircraft I AIAA PAPEB 82-1049] A82-40418 Third generation turbo fans A82-40964 ENGINE TBS1S 800 Shaft Horsepower Advanced Technology Demonstrator Engine A82-40520 Besearch on the behavior of a turbojet engine during internal and external disturbances with respect to early recognition of damage German thesis A82-40561 Axisymmetric approach and landing thrust reverser impacts on usage and LCC life cycle cost A82-40892 The nonsynchronous whirls of the turbine rotor in aerojet engines A82-40944 Intake svirl - A major disturbance parameter in engine/intake compatibility A82-41018 Hater ingest ion into axial flow compressors. Part 3: Experimental results and discussion [AD-A114830] N82-29326 ENVIBONBENT SIBOLATION NASA/FAA Helicopter ATC simulation investigation of BKAV/HLS instrument approaches A82-40535 Atmospheric electricity hazards analytical model development and application. Volume 2: Simulation of the lightning/aircraft interaction event [AD-A114016] , K82-29801 BNVIBOHBBNT SIHDIAIOES The design of a BPV ground station simulator A82-39750 BHVIBOHBENIAL TESTS Analyzing stable pad disturbances and design of a sensor vault to monitor pad stability [AIAA 82-1585] A82-39011 EHVIBCHJBHTS The work environment N82-29299 EPOXT BAXBIX COflfOSITES A one-shot autoclave manufacturing process for carton epoxy components A82-40935 EQUATIONS OF HOTIOS Computer-aided derivation of equations of motion for rotary-wing aeroelastic problems A82-40883 The nonsynchronous whirls of the turbine rotor in aerojet engines A82-40944 Beduced nonlinear flight dynamic model of elastic structure aircraft A82-41009 User's manual for the AHEEB flight path-trajectory simulation code [DE82-007004] S82-29343 EEBOB ANALYSIS Beduction and analysis of mode C altitude data collected at high altitudes over the continental United States [AD-A114655] B82-29276 Establishment of a rotor model basis [NASA-TP-2026] 1182-29311 ETHIL A1COH01 Ethanol production by vapor compression distillation [DE82-004892] N82-29393 EVASIVE ACTIONS Air-to-air missile avoidance [AIAA 82-1516] A82-38939 A-20. SOBJECT IBDEI FIBEB BEIBFOBCBD COflPOSITES EXHAUST EHISSIOS Two-dimensional model studies of tie impact of aircraft exhaust emissions on tropospiieric ozone £82-40124 EXHAOST BOZZLBS Performance of a 2D-CD nonaxisymmetric exhaust nozzle on a turbojet engine at altitude [AIAA PAPEE 82-1137] A82-40420 Application cf advanced exhaust nozzles for tactical aircraft A82-40889 EXPABDABLE STEOCtOEES Flight control systems for aerial targets A82-39745 BXPBBIHBHTAL EESIGS Applying advanced technology to flight station design A82-40887 EX1EBBAL ST08B SBP1EATIOB Wind tunnel studies of store separation vith load factor. Freedrops and captive trajectories H82-30261 BX5BAPOLATIOB Analytic extrapolation to full scale aircraft dynamics [AIAA PAPEE 82-1387] A82-391Q3 F-1Q AIBCBAFT NASA Dryden's experience in parameter estination and its uses in fligat test [AIAA PAPEE 82-1373] A82-39135 F-16 AIBCBAFT Terrain foilowing/terrain avoidance system concept development [AIAA PAPEIi 82-1518] A82-40428 Non-honeycomb F-16 horizontal stabilizer structural design A62-40936 F-111 AIBCBAF1 Comparative vertical iapact testing of the F/FB-111 crew restraint system and a proposed modification ~[AD-A113957] B82-28267 FABBICATIOB Design and fabrication of cocured composite hat-stiffened panels A82-40S78 FABBICS Technical and economic comparison of carbon fiber tape and woven fabric applications 482-40993 FAIL-SAFE SISIEHS Generic faults and design solutions for flight-critical systems [AIAA 82-1595] A82-38980 A preliminary laboratory evaluation of a reconfigarable integrated flight control concept [AIAA 82-1597] J82-38982 FAILOBE ABALISIS Prediction of fatigue crack grovth rates under variable loading using a simple crack closure nodel [NLB-HP-81023-U] B82-28685 FA1LOBE BODES Material identification for the design of composite rotary Hings A82-40937 The effect of intake flow disturbances on AEO compressor blade higa cycle fatigue in the Airbus A300 A82-40983 FALKBEB-SKAB EQDAIIOB Improved solutions to the Falkner-£kan boundary-layer eguation A82-38283 FAB BLADES National Transonic Facility (BTF) prototype fan blade fatigue test [AD-A114405] B82-28261 FASIBBEBS Fasteners for composite structures £82-39929 FATIGUE (HATBBIALS) 'Listening* systems to increase aircraft structural safety and reduce costs £82-39539 The effect of intake flow disturbances on APU compressor blade high cycle fatigue in the Airbus 1300 A82-40983 Principles of achieving damage tolerance with flexible maintenance programs for new and aging aircraft A82-41016 FATJGDE LIFE A roadmap toward a fatigue qualification process for modern technology helicopters A82-40542 Design and experimental verification of the OSB-flap structucture for BAL STOL aircraft Opper surface Blowing A82-40917 A crack growth model under spectrum loading A82-40961 FATIGUE IES1S Fasteners for composite structures A82-39929 A roadaap toward a fatigue qualification process for modern technology helicopters A82-40542 Application of a new hybrid material /ABALL/ in aircraft structures A82-40975 FAOil 10LEBAHCE Generic faults and design solutions for flight-critical systems (AIAA 82-1595] A82-38980 The Shiryayev sequential probability ratio test for redundancy management [AIAA 82-1623] A82-38998 Analytical design and validation of digital flight control system structure [AIAA PAPEB 82-1626] A82-40434 Problems related to the integration of fault tolerant aircraft electronic systems [BASA-CB-165926] N82-29022 FEASIBILITY ABALISIS Adaptive fuel control feasibility investigation A82-40519 FEEDBACK COSTBOL Hodal control of relaxed static stability aircraft [AIAA 82-1524] A82-38944 The use of differential pressure feedback in an automatic flight control system [AIAA 82-1596] A82-38981 Flight contrcl synthesis using robust output observers [ (AIAA 82-1575] A82-39016 Application of mnltivariable model following method to flight controller [AIAA PAPEB 82-1349] A82-39120 Design and analysis of a multivariable control system for a CCV-type fighter aircraft [AIAA PAPEB 82-1350] A82-39121 Design of a longitudinal ride-control system by Zakian's method of inequalities A82-41114 FIBEB COHPOSUES Technical and economic comparison of carbon fiber tape and woven fabric applications A82-40993 Design considerations and experiences in the use of composite material for an aeroelastic research wing [HASA-Tfl-83291] N82-28280 FIBEB BEIHFOBCED COMPOSITES The effect of hybrid composite materials on the dynamic characteristics of helicopter rotor blades A82-39263 A summary of weight savings data for composite VSTOL structure A82-40546 Material and process developments on the Boeing 767 A82-40902 Material identification for the design of composite rotary wings A82-40937 Application ,of a new hybrid material /ABALL/ in aircraft structures A82-40975 Sliced disc design - A composite conform concept for a turbo engine axial compressor A82-40995 1-21 FIGHTEB AIBCBAFT SUBJECT IHDEX Carbon fiber reinforceJ cciposite structures protected with metal surfaces against lightning strike damage [HBB-OD-340-82-0/I] H82-28364 FIGHIEB AIBCBAFT A design criterion for highly augmented fly-by-wire aircraft [AIAA 82-1570] .A'82-38969 An alternate method of specifying bandwidth for flying qualities [ ( A I A A 82-1609] A82-38988 Piloted simulator evaluation of a relaxed static stability fighter at high angle-cf-attack [AIAA PAPEE 82-1295] A82-39082 High angle-of-attack characteristics of a forward-swept wing f ighter configuration [ A I A A PAPEB 82-1322] A82-39099 The correlation of flijht test and analytic H-on-H air combat exchange ratios Hany-on-Bany [AIAA PAPEB 82-1328] A82-39105 Design and analysis of a moltivariable control system for a CCV-typa fighter aircraft [AIAA PAPEB 82-1350] A82-39121 Unmanned aircraft in future combat A62-3S728 Short range tactical Btd system A82-39730 Aerodynamic aspects of aircraft dynamics at high angles of attack /AGijjD lecture/ [ A I A A PAPEB 82-1363] A82-39836 Flying qualities requirements for rcll CAS systems [ A I A A PAPEB 82-1356] A82-40287 Flight experience with a backup flight-control system for the HiBAT research vehicle [ A I A A PAPEB 82-15111] A82-40429 Advanced aerodynamic design for fu ture combat aircraft A82-40879 Some aerodynamic/f lightiiechanic aspects for the design of future corneat aircraft 482-40880 A practical approach to the incorporation of technical advances ia avionics A82-40886 The evolution of display formats for advanced fighters using multinode color CET displays A82-40888 Application of advanced exhaust nozzles for tactical aircraft 482-40889 Advanced fighter technology integration program AFTI/F-16 482-40900 Tail versus canard configuration - An aerodynamic comparison with regard to the suitability for future tactical combat aircraft A82-40901 Spin behaviour of the filatus PC-7 lurbor Trainer A82-40979 Analytical study of vortex flaps on highly swept delta wings A82-41003(find-tunnel investigation ct vortex flaps on a highly swept interceptor configuration A82-41004 Intake swirl - A major disturbance parameter in engine/intake compatinility A82-41018 An improved propulsion system simulation technique for scaled wind tunnel icdel testing of advanced fighters A82-41019 low-speed characteristics of a fighter-type configuraticn at higa angles-of-attack and sideslip 482-41020 Bing design for supersonic cruise/transonic maneuver aircraft 482-41021 Advanced trending analysis/iDS data program [AD-A113511] N82-28286 A discussion of the flying guality requirements of a basic training aircraft [AD-4114805] H82-29318 FINITE DIFFBBEHCE TBBOBY. A finite difference nethod for the calculation of transonic flow about a wing, based on small perturbation theory [HLB-1B-81051-0] B82-28263 FIHITE E1EBEST HBTHOD Development of the advanced composite ground spoiler for C-1 medium transport aircraft A 82-39895 Finite element analysis for bearingless rotor blade aeroelasticity A82-40517 Cracks interacting with contact forces - A finite element study on loaded holes A82-40959 FIBE COHIEOI 0.S. Army remotely piloted vehicle program A82-39732 FIBE D A M A G E ' Evaluation of heat damage to aluminum aircraft structures A82-41141 Aircraft fire safety [AGABD-LS-123] 1182-29279 Aircraft fire mishap experience/crash fire scenario guantitation N82-29280 Aviation fuels-future outlook and impact on aircraft fire threat H82-29282 Fireworthiness of transport aircraft interior systems N82-29284 The development and applications of a full-scale wide body test article to study the behavior of interior materials during a postcrash fuel fire 1182-29285 Aircraft post crash fire reduction/survivability enhancement from a manufacturer's viewpoint 1182-29286 FIBE BI1IHGOISHBBS Aircraft post-crash fire fighting/rescue K82-29287 FIBE FIGHTIiG Smoke abatement system for crash rescue/fire training facilities [AD-A114380] 1182-28268 Aircraft fire safety [AGABD-LS-123] H82-29279 Aircraft fire mishap experience/crash fire scenario guantitation H82-29280 Aircraft post crash fire reduction/survivability enhancement from a manufacturer's viewpoint H82-29286 Aircraft post-crash fire fighting/rescue H82-29287 FIBE PBEVEHTIOB Fuel system protection methods H82-29283 Fireworthiness of transport aircraft interior systems H82-29284 The development and applications of a full-scale wide body test article to study the behavior of interior materials during a postcrash fuel fire H82-29285 FIBEPEOOFI1G The development and applications of a full-scale vide body test article to study the behavior of interior materials during a postcrash fuel fire N82-29285 FLAHB CA10BIHETEBS Beat release rate calorimetry of engineering plastics A82-41075 FLABBiBILITI Heat release rate calorimetry of engineering plastics A82-41075 FLAPS (COHTBOL S DBF ACES) Design and experimental verification of the DSB-flap structucture for HAL STOL aircraft Dpper Surface Blowing A82-40917 Flap-lag-torsional dynamics of extensional and inextensional rotor blades in hover and in forward flight [SASA-CB-169159] 1182-29312 FLEXIBLE IIIGS Inflated wings A82-40966 A-22 SUBJECT IBDBI FLIGHT OPTIBIZATTOH Variable geometry aerofoils as applied to the Beatty B-5 and B-6 sailplanes A82-40S68 FLIGHT CHiBlCIBBISIICS in alternate method of specifying randvidth for flying gualities £(Alii 82-1609] i82-38988 Investigation of low order lateral directional transfer function models for augmented aircraft [Alii 82-1610] A82-38989 Handling gualities criteria for flight path control of V/SIOL aircraft [Alii PiPEE 82-1292] 182-39081 In-Flight investigation of large airplane flying qualities for approach and landing [1I1A PAPEE 82-1296] i82-39083 Dnigue flight characteristics of the iD-1 obligue-wing research airplane [AIAA PIPES 82-1329] A82-39106 A ground-simulation investigation of helicopter decelerating instrument approaches A82-39118 Perspectives of the flying gualities specification [AIAA PAPEE 82-1354] A82-39123 Eingfin augmentation effects 182-40548 Prediction of high alpha flight characteristics utilizing rotary balance data i82-40953 FLIGHT COHDISIOBS Forward-swept wings add supersonic zip 182-38216 The operation of aircraft and helicopters in difficult meteorological and environmental conditions Russian book 182-39295 landem rotor helicopter characteristics in a continuous icing environment 182-40523 FLIGHT COHIBOL Adaptive filtering for an aircraft flying in turbulent atmosphere 182-38141 Future terminal area systems 182-38462 Design and flight testing of digital direct side-force control laws [AIAA 82-1521] 182-38941 Modal control of relaxed static stability aircraft [Alii 82-1524] 182-38944 A design criterion for highly augmented fly-by-wire aircraft [AIAA 82-1570] A82-38969 Generic faults and design solutions for flight-critical systaas [AIAA 82-1595] A82-38980 i preliminary laboratory evaluation of a reconfigurable integrated flight control concept [AIAA 82-1597] 182-38982 An alternate method of specifying randwidth for flying gualities [ ( A I A A 82-1609] A82-38988 The Shiryayev seguential probability ratio test for redundancy management [1111 82-1623] 182-38998 X-29A flight control system design experiences [AIAA 82-1538] A82-39003 Flight control synthesis using robust output observers [ ( A I A A 82-1575] A82-39016 Handling gualities criteria for flight path control of V/S1OL aircraft [1111 PAPEB 82-1292] A82-39081 Application of multivariable model following method to flight controller [1111 P1PEB 82-1349] 182-39120 Design and analysis of a multivariable control system for a CCV-typa fighter aircraft [1111 PIPES 82-1350] 182-39121 Perspectives of the flying gualities specification [1111 PIPEE 82-1354] A82-39123 Guidance for the use of eguivalent systems with HIL-F-8785C for aircraft flight control systems [AIAA PAPEB 82-1355] A82-39124 HASA Dryden's experience in parameter estimation and its uses in flight test [AI11 PIPES 82-1373] 182-39135 The system of 'objective control' A82-39245 Flying quality requirements for V/STOL transition [1IAA PAPER 82-1293] 182-40276 Flight-determined correction terms for angle of attack and sideslip [AIA1 PIPES 82-1374] A82-40290 Analytical design and validation of digital flight control system structure [ A I A A PIPES 82-1626] 182-40434 Design and construction of a flexible autonomic electronic display device for flight control 182-40569 Advanced fighter technology integration program AFTI/P-16 A82-40900 Optimal open-loop aircraft control for go-around maneuvers under wind shear influence 182-40943 Design integration of CCH/USB for a sea-based aircraft 182-40972 Electronic/electric technology benefits study avionics [N1S1-CB-165890] H82-28243 low cost development of INS sensors for expendable BPV control and navigation [1D-A112691] N82-28291 Hanuai reversion flight control system for A-10 aircraft: Pilot performance and simulator cue effects [AD-A113463] N82-28302 Geophysical flight line flying and flight path recovery utilizing the Litton LIN-76 inertial navigation system [DE82-005555] S82-29292 FLIGHT CBEiS Digital full authority controls for helicopter engines 182-40522 Flight attendant injuries: 1971-1976 flD-1114909] N82-29274 Operational test and evaluation handbook for aircraft training devices. Volume 1: Planning and management [AD-A112498] S82-29332 FLIGHT H1ZABDS Hind shear - Its effect on an aircraft and ways to reduce the hazard. II A82-38500 The operation of aircraft and helicopters in difficult meteorological and environmental conditions Bussian book A82-39295 Flight attendant injuries: 1971-1976 [AD-1114909] N82-29274 Atmospheric electricity hazards analytical model development and application. Volume 1: Lightning environment modeling [AD-1114015] N82-29800 Atmospheric electricity hazards analytical model development and application. Volume 2: Simulation of the lightning/aircraft interaction event [1D-A114016] , H82-29801 Atmospheric electricity hazards analytical model development and application. Volume 3: Electromagnetic coupling modeling of the lightning/aircraft interaction event [AD-A114017] 1882-29802 FLIGHT IHSTBUBEBIS Heads up display [HlSl-CiSE-Iia-12630-1] 1182-29319 System data communication structures for active-control transport aircraft, volume 2 [NASA-CB-165773-VOL-2] H82-29511 FLIGHT BECHABICS Some aerodynamic/flightmechanic aspects for the design of future combat aircraft A82-40880 FLIGHT OPTIHIZATIOS Flight management computers A82-39321 Optimal control application in supersonic aircraft performance 182-39374 The fourth dimension flight management system for airline operations A82-39540 1-23 FLIGHT PATHS SUBJECT IIDBI Optimization of flight with tilt Mings 182-40912 FLIGHT PATHS Handling qualities criteria for flight path control of V/STOL aircraft [AIAA PAPEB 82-1292] A82-39081 Analysis of in-trail fclloving dynamics of CDTI-eguipped aircraft Cockpit Displays of Traffic Information [ A I A A PAPEE 82-1330] A82-39107 An HLS with conputer aided landing approach [AIAA PAPEB 82-1352] A82-39122 The fourth dimension flight management system for airline operations A82-39540 A concept for IP-guidance of transport aircraft in the IMA Terminal Maneuvering Area A82-40942 Estimation of the number of in-flight aircraft on instrument flight rules A82-41117 Investigations concerned with shifting pilot activities to a higher hierarchical stage of flight control Garaan thesis A82-41453 Seduction and analysis of mode C altitude data collected at nigh altitudes over the continental United States [AD-A114655] 882-29276 Development of flying Qualities criteria for single pilot instrumant flight operations [BASA-CB-165932] 882-29288 User's manual for the 4<1IIB flight path-trajectory simulation code [DE82-007004] H82-29343 FLIGHT PLAHS PHCS - A commercial flight management computer system £AIAA 82-1515] A82-38938 FLIGHT BECOHDEBS Analysis of general-aviation accidents using ATC radar records [AIAA PAPEB 82-1310] A82-39091 Agricultural airplane nission time structure characteristics [HASA-TM-84470] 882-29329 FLIGHT SAFBTI The system of "objective ccntrol1 A82-39245 Instrument landing systems /ILS/ at airports of the German Democratic Republic A82-39248 FLIGHT SIBOLAIIOB Complete flexibility ana realism in radar simulation A82-38461 Pilot models for discrete maneuvers [AIAA 82-1519] A82-38940 Development and flight test evaluation of a pitch stability augmentation systen for a relaxed stability L-1011 [ A I A A PAPEB 82-1297] A82-39084 A ground-simulation investigation of helicopter decelerating instrument approaches A82-39118 Dse of rotary balance and forced oscillation test data in six degrees of freedom simulation [AIAA PAPEE 82-1364] A82-39129 Flight simulation studies en tie feasibility of laterally segmented approaches in an HLS environment A82-40941 The role of the scale parameter in service load assessment and simulation of aircraft flight A82-41011 Visual scene simulation concerning the landing of sporting aircraft in connection with investigations regarding the control and learning behavior of the pilot German thesis A82-41447 Manual reversion flight control system for A-10 aircraft: Pilot performance and simulator cue effects [AD-A113463] H82-28302 Computer program for analysis of spherical screen distortion [AD-A113136] 882-28309 FLIGHT SIBDLATOBS Simulator investigations of various side-stick controller/stability and control augmentation systems for helicopter terrain flight [AIAA 82-1522] A82-38942 Terrain following/terrain avoidance systen concept development [AIAA PAPEB 82-1518] A82-40428 Operational test and evaluation handbook for aircre* training devices. Volume 3: Operational suitability evaluation [AD-A112569] M82-28306 Development of flying qualities criteria for single pilot instrument flight operations [HASA-CB-165932] N82-29288 Operational test and evaluation handbook for aircraft training devices. Volume 1: Planning and management [AD-A112498] N82-29332 FLIGHT STABILITY TESTS Piloted simulator evaluation of a relaxed static stability fighter at high angle-of-attack [AIAA PAPEB 82-1295] A82-39082 NASA Dryden's experience in parameter estimation and its uses in flight test [AIAA PAPEE 82-1373] A82-39135 FLIGHT TEST IISIBDHBHTS A unique flight test facility - Description and results A82-40925 FLIGHT TEST VEHICLES A unique flight test facility - Description and results A82-40925 FLIGHT TESTS Design and flight testing of digital direct side-force control lavs [AIAA 82-15i1] A82-38941 The ideal controlled element for real airplanes is not K/s [ A I A A 82-1606] A82-38986 Avoiding the pitfalls in automatic landing ccntrol system design [AIAA 82-1599] A82-39013 Development and flight test evaluation of a pitch stability augmentation systeo for a relaxed stability L-1011 [AIAA PAPEB 82-1297] A82-39084 A simple, low cost application of a flight test parameter identification system [AIAA PAPEB 82-1312] A82-39093 The correlation of flight test and analytic M-on-B air combat exchange ratios Many-on-Hany [AIAA PJPEB 82-1328] A82-39105 Unique flight characteristics of the AD-1 oblique-Ming research airplane [AIAA PAPEE 82-1329] A82-39106 Analysis of an airplane windshield anti-icing system [AIAA PAPEB 82-1372] A82-39134 Evaluation of CFBP prototype structures for aircraft A82-39892 An evaluation of vertical drag and ground effect using the BSBA rotor balance systeo Botor Systems Besearch Aircraft A82-40510 Flight test evaluation of a video tracker for enhanced offshore airborne radar approach capability A82-40531 Besults of the AH-64 Structural Demonstration A82-40551 Design and flight testing of a digital optimal control general aviation autopilot A82-40906 A concept for ID-guidance of transport aircraft in the IMA Terminal Maneuvering Area A82-40942 Advanced trending analysis/EDS data program [&D-A113511] H82-28286 Methodology for determining elevon deflections to trio and maneuver the DAST vehicle with negative static margin [HASA-TH-84499] 882-28299 Geophysical flight line flying and flight path recovery utilizing the Litton LTN-76 inertial navigation system [DE82-005555] 882-29292 SUBJECT IBDEI FUEL PBODDCTIOI FLIGHT TIBE Agricultural airplane mission time structure characteristics [HASA-TS-84470] H82-29329 FLIGHT TBAIHING Operational test and evaluation handbook for aircrew training devices. Volume 3: Operational suitability evaluation [AD-A112569] S82-28306 Inflight IPS procedures sinulator [KAS4-C4SE-KSC-11218-1 ] H82-29331 Operational test and evaluation handbook for aircraft training devices. Volume 1: Planning and managenent [4D-4112498] N82-29332 FLIGHT VEHICLES Primary-data devices Bussian book A82-39279 FLOS CHABiCTBBISTICS Symposium on lions wita Separation, Stuttgart, Best Germany, Novembar 23-25, 1981, Beports A82-38781 On embedded flow characteristics of sharp edged rectangular Kings [LOG-C4712] N82-29263 FLOW DISIOBTIOH Research on the behavior of a turbojet engine daring internal and external disturbances with respect to early recognition of damage German thesis 482-40561 Fluctuating forces and rotor noise due to distorted inflow 482-40945 Intake swirl - A major disturbance parameter in engine/intake compatibility 482-11018 FLOH. DISTRIBUTION Close-coupled canard-wing vortex interaction and Beynolds stress acquisition [AIAA PAPEB 82-1368] A82-39132 Effect of tip vanes on the performance and flow field of a rotor in nover A82-40511 Aerodynamic interactions retween a 1/6-scale helicopter rotor and a body of revelation A82-40947 Spanwise distribution of vortex drag and leading-edge suction in subsonic flow A82-41005 FLOi HEASOBEHENT Measuring the flow properties of slotted test-section walls [FFA-135] H82-28571 FLOH THEOBI Calculation of level flow using radial grating 482-38922 The rectangular wing with semiinfinite span in nonlinear theory A82-39359 FLOi VELOCITI Measurements of velocity distributions in the leading edge vortex cf a delta wing by the laser-Doppler procedure A82-38786 FLOH VISUALIZATION An experimental investigation of leading-edge spanwise blowing A82-40988 FLUID INJECTION Turbulent boundary layer on a porous surface with injection at various angles to the wall A82-39482 FLOTTEB Bobust Kalman filter design for active flutter suppression systems A82-38442 Design of compensated flutter suppression systems A82-40904 Design considerations and experiences in the use of composite material for an aercelastic research wing [NASA-TH-83291] N82-28280 FLOTTEB ANALISIS Dynamic stability of flexible forward swept wing aircraft [AIAA PAPEB 82-1325] A82-39102 Finite element analysis for bearingless rotor blade aeroelasticity 482-40517 FIT BI BIBB COHTSOL A design criterion for highly augmented fly-by—wire aircraft [AIAA 82-1570] A82-38969 Analytical design and validation of digital flight control system structure [AIAA PAPEB 82-1626] A82-40434 Design and experience with a low-cost digital fly-by-wire system in the SAAB JA37 Viggen A/C A82-10905 FOAHS Aircraft post-crash fire fighting/rescue K82-29287 FOBCED VIBBATIOI Dse of rotary balance and forced oscillation test data in six degrees of freedom simulation [AIAA PAPEB 82-1364] A82-39129 Limiting performance of nonlinear systems with applications to helicopter vibration control problems [AD-A113239] H82-28301 FOBGIHG International aviation (selected articles) [AD-A114422] 1182-28245 FOBBING TECHNIQUES Adaptation of pultrusion to the manufacture of helicopter components A82-40537 FBEB FLOI Aerodynamic behavior of a slender slot in a wind tunnel wall 482-38281 FUEL COBSOfllTIOJ Fuel conservation: The airline - 4TC A82-38464 Minimization of the total costs incurred in the employment of passenger jet aircraft 482-39247 Flight management computers 482-39321 The fourth dimension flight management system for airline operations 482-39540 Hini-EPV propulsion 482-39736 Beguirements and trends in fuel consumption in transport mission with aircraft and surface vehicles 482-40956 4erodynamic concepts for fuel-efficient transport aircraft 482-40957 Third generation turbo fans 482-40964 Aircraft design for fuel efficiency 482-40973 CF6 jet engine performance improvement: High pressure turbine active clearance control [SAS4-CB-165556] N82-28297 FUEL CCNTBOL Adaptive fuel control feasibility investigation 482-40519 FUEL PBODOCTIOB An exploratory research and development program leading to specifications for aviation turbine fuel from whole crude shale oil. Part 1: Preliminary process analyses [AD-A112681] H82-28462 An exploratory research and development program leading to specifications for aviation turbine fuel from whole crude shale oil. Part 2: Process variable analyses and laboratory sample production [AD-A112682] 1182-28463 An exploratory research and development program leading to specifications for aviation turbine fuel from whole crude shale oil. Part 3: Production of specification of JP-4 fuel from geokinetics shale oil [AD-A112683] N82-28464 Ethancl production by vapor compression distillation [DE82-004892] H82-29393 United States Air Force shale oil to fuels, phase 2 [AD-A114531] 1182-29476 »-25 FUEL SYSTEMS SOBJECT IIDBX FUEL ST.STEBS Fuel system protection methods H82-29283 FOSELAGBS Toward all-composite helicopter fuselage 482-38223 Numerical solution of i problem concerning transonic flow past a wing-fuselage configuration 482-39996 Design and fabrication of a composite rear fuselage for the UH-60 /Black Hank/ 482-40544 Fuselage effects in leading edge vertex flap aerodynamics 482-41006 An initial look at the supersonic aerodynamics of twin-fuselage aircraft concepts £82-41008 GiS GEBEBAIOBS Comparison of HP turbine 'deep blade design' effects in turbofan engine gas generators ¥ith different bearing structure configurations A82-409S6 GAS TOBBIHE EHG1HES Application of the sequential optimization method to the tuning of the natural frequencies of gas-turbine engine compressor blades A82-39399 The use of analog computers in solutions of inverse problems of heat conduction for tie identification of boundary conditions on the surfaces of gas-turbine-engine parts on the basis of temperature-measurement results 482-39167 GEARS Beliability model for cj.anetary gear [HAS4-TM-82859] N82-28643 GEBEBAL AVIATION AIBCBAFT Analysis of general-aviation accidents using ATC radar records [4144 P4PEE 82-1310] 462-39091 Parameter estimation applied to general aviation aircraft - 4 case stjdy [AIAA PAPEI 82-1313] 482-39094 Analysis of an airplane windshield anti-icing system [AIAA PAEEB 82-1372] 482-39134 Propulsion opportunities fcr future commuter aircraft [AIAA PAPEB 82-1049] 482-40418 Sport aircraft Bussian book 482-40463 Design and flight testing of a digital optimal control general aviation autopilot 482-40906 Dual wing, swept forward swept rearward wing, and single wing design optimization for high performance business airplanes 482-40931 Assessaent of advanced technologies for high performance single-engine business airplanes 482-40932 Operation V10F - Development of a composite material wing 482-40934 Hind-tunnel investigation of a full-scale canard-configured general aviation aircraft 482-41024 Visual scene simulation concerning the landing of sporting aircraft in connection with investigations regarding the control and learning behavior of the filot German thesis 482-41447 General aviation activity and avionics survey [AD-A112924] 1182-28244 Flight evaluation of LCBAH-C in the State of Vermont [HASA-Tfl-84711] H82-28278 F4A aviation forecasts-fiscal years 1982-1993 [AD-4114696] B82-29261 Crashworthiness studies; Cabin, seat, restraint, and injury findings in selected general aviation accidents [4D-4114878] H82-29275 6EODIHABICS Baseline monitoring using aircraft laser ranging spaceborne laser simulation and aircraft laser tracking [H&SA-TH-73298] 1182-28690 GEOLOGICAL SOBVEIS Geophysical flight line flying and flight path recovery utilizing the Litton LTH-76 inertial navigation system £DE82-005555] B82-29292 6EOHEIBIC BBCTIFICATIOH (IHAGBBT) Scanner imaging systems, aircraft N82-28715 6EOPHISICS Geophysical flight line flying and flight path recovery utilizing the Litton LTN-76 inertial navigation system [DE82-005555] N82-29292 GLASS FIBEB BEIiFOBCED ELASTICS Adaptation of pultrusion to the manufacture of helicopter components 482-40537 Determination of load spectra and their application for keeping the operational life proof of sporting airplanes 482-41010 Development of materials and manufacturing technology over the next 20 years: Composite materials [ BBB-DD-341-82-0] H82-28365 GLIDE PATHS Flight simulation studies on the feasibility of laterally segmented approaches in an MLS environment A82-40941 Terminal area automatic navigation, guidance, and control research using the Microwave Landing System (HIS). Part 4: Transition path reconstruction along a straight line path containing a glideslope change waypoint [K4S4-CB-3574-PT-4] U82-28269 GUDBBS Dynamic energy transfer between wind and aircraft A82-40939 Design and tests of airfoils for sailplanes with an application to the ASB-19B 482-40967 Variable geometry aerofoils as applied to the Beatty E-5 and B-6 sailplanes 482-40968 Determination of load spectra and their application for keeping the operational life proof of sporting airplanes A82-41010 GBAPHITE-EEOXT. COMPOSITES Developments on graphite/epozy T-2 nose landing gear door A82-39893 Development of the advanced composite ground spoiler for C-1 medium transport aircraft A82-39895 Development status of a composite vertical stabilizer for a jet trainer 482-39897 Mon-honeycomb F-16 horizontal stabilizer structural design 482-40936 Design and fabrication of cocured composite hat-stiffened panels 482-40978 Application of composite materials and new design concepts for future transport aircraft 482-40994 6BOUHD BASED COiTBOL Flight control systeis for aerial targets 482-39745 The design of a BPV ground station simulator 482-39750 GBOOIO EFFECT (AEIODTIAHJCS) An evaluation of vertical drag and ground effect using the BSB4 rotor balance system Botor Systems Research Aircraft 482-40510 GfiOOHO SfATIOBS Flight control systems for aerial targets 482-39745 The design of a BPV ground station simulator 482-39750 A-26 SDBJECT IBDEX HBLICOPTEB DESIGH 6BODBD SOPPOBI SISTBHS U.S. Army remotely piloted vehicle supporting technology program 482-39739 GBOOBD TESTS Error minimization an ground vibration testing of helicopter structures A82-40550 GB001D HATE PBOPAGAHCH Electromagnetic Propagation Problems in the Tactical Environment [AGABD-I.S-120] H82-29527 GBOOHD-AIB-GBOOID COflflOHICATICB VHP radio link for ground-air-ground coomunications using an integrated voice-data modulation A82-38405 Communications H82-29302 GOIDAHCE SBBSOBS Analyzing stable pad disturbances and design of a sensor vault tc monitor pad stability [AIAA 82-1585] A82-39011 Fixed pattern noise correction for staring arrays in guidance systems A82-39190 A terrain following systea, an algorithm and a sensor A82-39740 Sensor stabilisation raguirements of BPV's - A simulation study A82-39741 GODS (OBDHABCE) Kinematic investigation Hughes Helicopter 7.62mm chain gun [AD-A113114] N82-28287 GDST ALLEVIATOBS Gust load alleviation on Airbus A 300 A82-40881 GUST LOADS The effects of atmospharic turbulence on a guadrotor heavy lift airship[AIAA 82-1542] A82-39009 Gust response of commercial jet aircraft including effects of autopilot operation[BASA-CB-165919] B82-28266 The determination of gust leads on ncnlinear aircraft using a power spectral density approach [BLB-TB-80123-U] B82-28303 Prediction of fatigue crack growth rates under variable loading using a simple crack closure model [BLB-HP-81023-U] N82-28685 Automated optimum design of wing structures. Deterministic and probabilistic approaches[BASA-T»-84475] H82-29317 H HABDBOOKS Operational test and evaluation handbook for aircraft training deuces. Volume 1: Planning and management [AD-A112498] B82-29332 HABBTBSSBS Comparative vertical iapact testing of the F/FB-111 crew restraint system and a proposed modification [AD-A113957] B82-28267 Feasibility study of a 270V dc flat cable aircraft electrical power distributed system [AD-A114026] B82-28552 HABKEB SIDDELEI AIBCBAFI U.S. Marine Corps AV-8A maintenance experience [AIAA PAPEB 81-2657] A82-38446 HEAD-OP DISPLAYS Micro-heads-up display A82-40533 Design study for a low-distcrtion holographic HOD [AD-A113982] N82-28292 Heads up display [NASA-CASE-LAB-12630-1] H82-29319 BEAT TBABSFBfi Cooled variable nozzle radial turbine for rotor craft applications [BASA-CB-ie5397] B82-29323 BEAVI LIFT AIBSHIPS The effects of atmospheric turbulence on a guadrotor heavy lift airship [AIAA 82-1542] A82-39009 Performance characteristics of a buoyant quad-rotor research aircraft A82-40974 HEIGHT A recursive terrain height correlation system using multiple model estimation techniques [AIAA 82-1513] A82-38937 BELICOPTEB CCBTBOL Simulator investigations of various side-stick controller/stability and control augmentation systems for helicopter terrain flight [AIAA 82-1522] A82-38942 A ground-simulation investigation of helicopter decelerating instrument approaches A82-39118 Adaptive fuel control feasibility investigation A82-40519 Concept demonstration of automatic subsystem parameter monitoring military helicopter cockpit instrumentation A82-40530 Avionics systems for helicopter integration A82-40534 NASA/FAA Helicopter ATC simulation investigation of BBAV/H1S instrument approaches A82-40535 BELICOPTEB DESIGi Composite use on helicopters A82-38222 Toward all-ccmposite helicopter fuselage A82-38223 The need for a dedicated public service helicopter design A82-38422 The effect of hybrid composite materials on the dynamic characteristics of helicopter rotor blades A82-39263 Short range tactical BPU system A82-39730 American Helicopter Society, Annual Forum, 38th, Anaheim. CA, Hay 4-7, 1982, Proceedings A82-40505 A new Transonic Airfoil Design Method and its application to helicopter rotor airfoil design A82-40507 Becent advances in rotor technology at Boeing Vertol A82-40508 Helicopter vibration reduction by rotor blade modal shaping A82-40514 Correlation of predicted vibrations and test data for a wind tunnel helicopter model A82-10515 Sikorsky ACAP preliminary design Advanced Composite Airframe Program A82-40526 Conceptual design of the LHX integrated cockpit A82-40527 The YAH-64 empennage and tail rotor - A technical history A82-40528 Future helicopter cockpit design A82-40529 Adaptation of pultrusion to the manufacture of helicopter components A82-40537 Development of the Sea King composite main rotor blade A82-40539 Computer aided coordinate measuring systems in engineering design of helicopter components A82-40540 A roadmap toward a fatigue qualification process for modern technology helicopters A82-40542 Optimum structural design for helicopters A82-40543 Design and fabrication of a composite rear fuselage for the OH-60 /Black Hawk/ A82-40544 Structural design of a crashworthy landing gear for the AH-64 Attack Helicopter A82-40547 Bingfin augmentation effects A82-40548 A-27 HELICOPTEB EH6IHES SUBJECT IHDEX Results of the AH-61 Structural Demonstration A82-40551 Material identification for the design of composite rotary wings A82-40937 HELICOPTBB BHGIHES Civil helicopter propulsion system reliability and engine monitoring technology assessments 282-40518 Adaptive fuel control feasibility investigation 482-40519 800 shaft Horsepower Advanced Technology Demonstrator Engine A82-40520 TF34 Convertible Engine System Technology Program A82-40521 Digital full authority controls for helicopter engines A82-40522 Support of the HH-65A - Tie impact of advanced technology of VTOL systems upon existing product support 482-40541 HELICOPTEE PEBFOBB4HCE Flight dynamics of rotorcraft in steep high-g turns [A1AA PAPEB 82-1345] A82-39117 Rationalization of the maintenance process for helicopter Ka-26 482-39246 The operation of aircraft and helicopters in difficult Eeteorclogical and environmental conditions Russian bcok A 82-3 92 95 Short range tactical BfH system 482-39730 An evaluation of vertical drag and ground effect using the ESBA rotor balance system Rotor Systems Research Aircraft A82-40510 Tandem rotor helicopter characteristics in a continuous icing environment 482-40523 An evaluation of helicopter autorotation assist concepts 482-40524 Flight test evaluation of a video tracker for enhanced offshore airborne radar approach capability 482-40531 Avionics systems for haliccpter integration A82-40534 Support of the hH-65A - The impact of advanced technology of VIOL systems upon existing product support A82-40541 Error minimization in jround vibration testing of helicopter structures 482-40550 The prediction of helicopter rotor discrete freguency noise 482-40553 Dynamic surface measurements on a model helicopter rotor during blade slap at high angles of attack 482-40555 Helicopter model scale results of rlade-vortex interaction impulsive ncise as affected by blade planform A82-40556 BELICOPTEB TAIL EOTOBS The T.AH-64 empennage and tail rotor - 4 technical history 482-40528 Bingfin augmentation effects 482-40548 HEJ.ICOPTEB IAKBS A simplified approach to tie free wake analysis of a hovering rotor A82-38474 An experimental and nunerical study of 3-D rotor wakes in hovering flight 482-40946 HELICOPTEBS Evaluation of an asymptotic method fcr helicopter rotor airloads A82-40509 Micro-heads-up display 482-40533 Improved 243 (JHz homing antenna system for use on helicopters £ JUB-BP-81022-0] N82-28276 Evaluations of helicopter instrument-flight handling qualities fAD-4114004] H82-28285 Kinematic investigation Hughes Helicopter 7.62mm chain gun (AD-A113114] H82-28287 HISS calibration, ice phobics and F44 B/D evaluations [AD-4114435] N82-28289 Limiting performance of nonlinear systems with applications to helicopter vibration control problems [4D-4113239J N82-28301 Reliability model for planetary gear [H4SA-TH-82859] N82-28643 HIBBAHCHIES Investigations concerned with shifting pilot activities to a higher hierarchical stage of flight control German thesis A82-41453 BIGB ALTITODE Reduction and analysis of mode C altitude data collected at high altitudes over the continental Dnited States [AD-A114655] N82-29276 BIGB ASPECT BATIO Beans for controlling aerodynamically induced twist [N4SA-CASE-L4B-12175-1] H82-28279 HIGH GBAVITZ EHVIBOHBESTS Flight dynamics of rotorcraft in steep high-g turns [4IAA PAPEB 82-1345] ' A82-39117 HIGH SPEED Summary and recent results from the NASA advanced high-speed propeller research program [AIA4 P4PEB 82-1119] 482-40419 4 semiempirical high-speed rotor noise prediction technique 482-40554 HOLE DISIRIBOTIOH (HECHAHICS) Cracks interacting with contact forces - A finite element study on loaded holes 482-40959 HOLOGBAPHIC IHTEBFBBOBETBI Nondestructive testing in aircraft construction using holographic methods 482-40977 High-sensitivity holographic plates PL-3H 482-41575 BOLOGBAEHI Design study for a lov-distortion holographic HOD £40-4113982] N82-28292 HOMISG DEFICES Improved 243 MHz homing antenna system for use on helicopters [NLB-BP-81022-0] N82-28276 HOBIZOHTAI FLIGHT Some comments on the prediction of forward flight effects on jet noise [BPIS-20/1981] M82-29118 Flap-lag-torsional dynamics of extensional and inextensional rotor blades in hover and in forward flight [N4SA-CB-169159] N82-29312 BOBIZOHT4L TAIL SDBFACES Tests of CFBP spar/rib models with corrugated web A82-39890 Fabrication of CFBP prototype structure for aircraft horizontal tail leading edge slat rail A82-39896 HOVEBIiG A simplified approach to the free wake analysis of a hovering rotor A82-38474 Flying guality requirements for V/STOI transition [AIAA PAPEB 82-1293] A82-40276 Theory and application of optimum airloads to rotors in hover and forward flight 482-40506 Effect of tip vanes on the performance and flow field of a rotor in hover 482-40511 An investigation of scale model testing of VTOL aircraft in hover 482-40911 4-28 SDEJECT INDEX IBGESTION (ENGINES) An experimental and nunerical study of 3-D rotor vakes in hovering flight 482-40946 Flap-lag-torsional dynamics of. extensional and inextensional totor tlades in hover and in forward flight [8AS4-CB-169159] H82-29312 HOVEHIiG STABILITY in analysis of a nonlinear instability in the , implementation of a >ICL control system during hover [4144 82-1611] 482-38990 An experimental investigation of a bearingless model rotor in hover 482-40512 Finite element analysis for bearingless rotor blade aeroelasticity 482-40517 HOBS Investigation of a rotor system incorporating a constant lift tip [N4S4-CB-166261] B82-29271 HUUAN F4CTOBS BNGINBEBING The effects of the delays on systems subject to manual control 482-38943 The system of 'objective control1 482-39245 Evaluation of an automatic subsystem parameter monitor for aircraft 482-40552 The evolution of display formats for advanced fighters using multimode color C£T displays 482-40888 Human factors in air traffic control [AG4BE-4G-275] 882-29293 The air traffic control system 882-29294 Human factors contributions to air traffic control systems 1182-29295 Han as a system component 882-29296 The work environment N82-29299 Displays 882-29300 Controls N82-29301 Additional functions vithin the air traffic control system N82-29309 Future trends and problems 882-29310 HUH4H PEBFOBBABCE Hunan capabilities and liiitations in systems B82-29297 HDHAB BEACTIOHS Aircraft fire safety [4G4BD-LS-123] 882-29279 Human response to fire N82-29281 HIBBID SIHOCTUBIS The effect of hybrid composite materials on the dynamic characteristics of helicopter rotor blades 482-39263 HXDBADLIC TEST IOHHEXS Use of the cavitation tunnel at the Dutch Naval Experiment station (ESP), Hageningen for the determination of the acoustic source strength of propeller cavitation [TPD-908-720] 882-29116 HZDBOCABBON FOE1S Atnospheric chemistry of hydrocarbon fuels. Volume 2: Outdoor chamber data tabulations. Part 1 [4D-4113665] 1182-28842 HIGBOSCOPICITI Becent development in nygrcthemoviscoelastic analysis of composites H82-28676 HYSTERESIS Aerodynamic aspects of aircraft dynaaics at high angles of attack /AGABD lecture/ [AIAA P4PEB 82-1363] 482-39836 ICE FOEH4TIOI Tandem rotor helicopter characteristics in a continuous icing environment 482-40523 HISS calibration, ice phobics and F44 B/D evaluations [4D-4114435] . 882-28289 An evaluation of the Bosemount ice detector for cloud water content measurements [PB82-158833] 882-29321 ICE PBEVEBTIOH 4nalysis of an airplane windshield anti-icing system [4144 P4PEB 82-1372] 482-39134 IDEAL FLUIDS Calculation of level flow using radial grating 482-38922 IBAGE PBOCBSSIHG Scanner iaaging systems, aircraft 882-28715 IMAGING TECHNIQUES Computer program for analysis of spherical screen distortion [AD-4113136] 882-28309 IHPACT LOADS • The behavior of composite thin-walled structures in dynamic buckling under impact 482-40976 IMPACT TES1S Comparative vertical impact testing of the F/FB-111 crew restraint system and a proposed modification [4D-4113957] H82-28267 18-FLIGHT MCBIT.OEIBG Minimal order time sharing filters for IMS in-flight alignment 482-38439 'Listening* systems to increase aircraft structural safety and reduce costs 482-39539 Concept demonstration of automatic subsystem parameter monitoring military helicopter cockpit instrumentation 482-40530 INCOHPBESSIBLE BOOBDABY LAY.EB Experimental and theoretical studies of three-dimensional turbulent boundary layers on an empennage of a typical transport airplane 482-40955 IHEBTIAL NAVIGATION Minimal order time sharing filters for INS in-flight alignment 482-38439 Geophysical flight line flying and flight path recovery utilizing the Litton LTB-76 inertial navigation system [DE82-005555] S82-29292 IBFLAXABLE SIBBCTDBES Inflated wings 482-40966 IBFOBHATICB FL08 Communications B82-29302 INFOBBATION SYSTBHS Preliminary design of an advanced integrated power and avionics information system A82-40907 INFBABID DETECTOBS Fixed pattern noise correction for staring arrays in guidance systems 482-39190 INFBABED BABIOHEIEBS Application of an optical data link in the airborne scanning system 482-39275 INFBABED TBACKING Algorithm development for infra-red air-to-air guidance systems 482-39191 IHGESTION (ESGIBBS) Hater ingestion into axial flow compressors. Part 3: Experimental results and discussion [4D-4114830] N82-29326 Effect of water on axial flow compressors. Part 2: Computational program [4D-4114831] 882-29327 A-29 IHJDBIES SDBJECT IHDBX IBJOBIES Flight attendant injuries: 1971-1S76 [AD-A114909] B82-29274 Annual review of aircraft accident data: OS general aviation calendar year 1S79 [PB82-136250] B82-29278 INLET FLOi A summary of ?/S10L inlet analysis methods A82-40921 A summary of v/STOL inlet analysis methods [BASA-TM-82885] B82-28249 IBLEI PBESSOBE Inlet and airframe compatirility for a V/SICI fighter/attack aircraft with top-mounted inlets A82-4C9C8 IHSPECTIOH Computer aided coordinate leasuring systems in engineering design of helicopter components A82-40540 Principles of achieving damage tolerance with flexible maintenance programs for new and aging aircraft A82-41016 Method for refurbishing and processing parachutes [NASA-CASE-KSC-11042-1] H82-29330 IHSTBOHBBI APPBOACH NASA/FAA Helicopter ATC siiulation investigation of BBAV/MLS instrument approaches A82-40535 Flight simulation studies en the feasibility of laterally segmented approaches in an MLS environment A82-40941 IHSTBOHBBT FLIGHT BOLES A ground-simulation investigation of helicopter decelerating instrument approaches A82-39118 Tandem rotor helicopter characteristics in a continuous icing environment A82-H0523 Estimation of toe number cf in-flight aircraft on instrument flight rules A82-41117 Evaluations of helicopter instrument-flight handling qualities [AD-A114004] • B82-28285 Development of flying jdalities criteria for single pilot instrument flight operations [HASA-CB-165932] N82-29288 Inflight IFB procedures sinulator [NASA-CASE-KSC-11218-1 ] N82-29331 IHSTBOBBHT LABDIBG SXSTBHS Instrument landing systems /ILS/ at airports of the German Democratic Eefublic A82-39248 IHTAKE SISTBHS The effect of intake flow disturbances on APD compressor blade higo cycle fatigue in the Airbus A300 A82-409E3 IHTEBFEBE1CE DBAG The use of small strakas to reduce interference drag of a low wing, twin engine airplane f A I A A PAPEB 82-1323] A82-39100 IHTEBHAL COflBUSTIOH EBGIHIS Hini-BPV propulsion A82-39736 IITEBBATIOHAL COOPBBAIIOH Engineering aspects of international collaboration on Tornado A82-40878 IHVISCID FLOI Numerical solution of a problem concerning transonic flow past a Xing-fuselage configuration A82-39996 IOHOSPHBBIC F-SCA5TEB PBOPAGATIOB Electrooagnetic Propagation Probleis in the Tactical Environnent [AGAED-LS-120] B82-29527 JET AIBCBAFT D.S. flanne Corps AV-8A maintenance experience [AIAA PAPEB 81-2657] A82-38446 Ninimization of the total costs incurred in the enployment of passenger jet aircraft A82-39247 Development status of a composite vertical stabilizer for a jet trainer A82-39897 Tvo-dimensional model studies of the impact of aircraft exhanst emissions on tropospheric ozone A82-40124 Operation V10F - Development of a composite material wing A82-40934 Analysis of jet transport wings with deflected control surfaces by using a combination of 2- and 3-D methods A82-41022 Cost response of commercial jet aircraft including effects of autopilot operation [NASA-CB-165919] 882-28266 Computer enhanced analysis of a jet in a cross-stream U82-29555 JET AIBCB1FT BOISE Static noise tests on modified augmentor wing jet STCL research aircraft [SASA-TH-81231] B82-28295 The effect of barriers on wave propagation phenomena: Hith application for aircraft noise shielding [BASA-CB-169128] N82-29111 Some continents on the prediction of forward flight effects on jet noise [HPIS-20/1981] H82-29118 JET ENGIHE fOELS An exploratory research and development program leading to specifications for aviation turbine fuel from whole crude shale oil. Part 1; Preliminary process analyses [AD-A112681] B82-28462 An exploratory research and development program leading to specifications for aviation turbine fuel from whole crude shale oil. Fart 2: Process variable analyses and laboratory sample production [AD-A112682] B82-28463 United States Air Force shale oil to fuels, phase 2 [AD-A114531] N82-29476 JET E1GI1ES Bedundant control unit for an advanced multispool engine A82-40998 B747/JT9D flight loads and their effect on engine running clearances and performance deterioration; BCAC BAIL/P and IA JT9D engine diagnostics programs [HASA-CB-165573] N82-28296 CF6 jet engine performance improvement: High pressure turbine active clearance control [NASA-CB-165556] B82-28297 Hater ingestion into axial flow compressors. Part 3: Experimental results and discussion [AD-A114830] B82-29326 Effect of water on axial flow compressors. Part 2: Computational program [AD-A114831] N82-29327 JET FLOI Ming-tip jets aerodynamic performance A82-40987 Aerodynamics of an airfoil with a jet issuing from its surface [HASA-Tfl-84825] N82-29267 JOISTS (JOBCIIOBS) Fasteners for composite structures A82-39929 Theoretical and experimental investigation of joint-structural damping interaction for airplane construction A82-41013 JP-4 JET FUEL An exploratory research and development program leading to specifications for aviation turbine fuel from whole crude shale oil. part 3: Production of specification of JP-4 fuel from geokinetics shale oil [AD-A112683] B82-28464 K KALHAB FILTBBS Adaptive filtering for an aircraft flying in turbulent atmosphere A82-38441 i-30 SUBJECT IHDEX LIFT DBAG EiTIO Bobust Kalman filter design for active flutter suppression systems 482-38442 Research on an adaptive Kalman filter for solving the radar tracking problem German thesis 482-40562 KIBBH1TICS Kinematic investigation Hughes Helicopter 7.62mu chain gun [ AD-A113114] B82-28287 KDTT1-JODKOBSKI COHDI1IOH A summary of V/STOL ialet analysis methods [HASA-Tfl-82885] N82-28249 L-1011 AIBCBAFI Development and flight test evaluation of a pitch stability augmentation system for a relaxed stability L-1011 [AIAA PAPEB 82-1297] 482-39084 LA HI BAB BOOHD1BI I1IEB Aerodynamic development of laminar flow control on swept wings using distributed suction through porous surfaces A82-40894 External aerodynamic dasign for a laminar flow control glove on a Lockheed Jetstar viug A82-40895 LABI SAB FLOB Calculation of level flow using radial grating 482-38922 Observations and implications of natural laminar flow on practical airplane surfaces A82-40893 LAHIBAB FLO! AIBFOILS Aerodynamic develotment of laminar flow control on swept wings using distributed suction through porous surfaces 482-40894 External aerodynamic dasign for a laiinar flow control glcve on a Lockheed Jetstar winq A82-U0895 Progress at Douglas on laninar flow control applied to commercial transport aircraft A82-40958 LAHIBATES On the bearing strengths of CFBP laminates A82-39930 The promise of laminated metals in aircraft design 482-40903 Material identification for the design of composite rotary wings A82-40937 Application of a new hybrid material /ABALL/ in aircraft structures A82-40975 Design considerations and experiences in the use of composite material foi an aercelastic research wing [HASA-TM-83291] N82-28280 LAUDING The cost of noise reduction for departure and arrival operations of ccmercial tilt rotor aircraft [SlSA-Cfi-137803] S82-29316 LAHDJHG GEAB Developments on graphite/epoxy 1-2 nose landing gear door A82-39893 Touchdown technology large aircraft landing gear stress A82-40057 Structural design of a crashworthy landing gear for the AH-64 Attack Helicopter A82-40547 LAHD1HG LOADS Automated optimum design of wing structures. Deterministic and probatilistic approaches [NASA-TH-84475] N82-29317 LABDIBG SIBOLATIOH Visual scene simulation concerning the landing of sporting aircraft in connection with investigations regarJing the control and learning behavior of the pilot German thesis A82-41447 LASEB DOPPLBB VELOCIHETBBS Heasurements of velocity distributions in the leading edge vortex of a delta wing by the laser-Doppler procedure A82-38786 LASEB GOIDAHCE O.S. Army remotely piloted vehicle program A82-39732 LASEB BAHGE FIHDEBS Badars for DBA A82-39742 Baseline monitoring using aircraft laser ranging spaceborne laser simulation and aircraft laser tracking [HASA-TH-73298] H82-28690 LASEBS Nearfield aerodynamics and optical propagation characteristics of a large-scale turret model [AD-A113910] H82-28624 LATEBAL CCBTBOL The ideal controlled element for real airplanes is not K/s [AIAA 82-1606] A82-38986 Investigation of low order lateral directional transfer function models for augmented aircraft £ A I A A 82-1610] A82-38989 Flying qualities requirements for roll CAS systems [AIAA PAPEB 82-1356] A82-40287 LADHCHEBS U.S. Army remotely piloted vehicle supporting technology program A82-39739 LEADING EDGE FLAPS Fuselage effects in leading edge vortex flap aerodynamics A82-41006 LEADING EDGE SLA1S Fabrication of CFBP prototype structure for aircraft horizontal tail leading edge slat rail A82-39896 LEADIHG EDGES Investigations regarding vortex formation at wings with bent leading edges A82-38783 Leading edge separation at delta wings with curved leading edges in supersonic flow A82-38784 Measurements of velocity distributions in the leading edge vortex of a delta wing by the laser-Doppler procedure A82-38786 Lateral aerodynamics of delta wings with leading edge separation (AIAA PAPEB 82-1386] A82-39142 Inflated wings A82-40966 An experimental investigation of leading-edge spanwise blowing A82-40988 Spanwise distribution of vortex drag and leading-edge suction in subsonic flow A82-41005 LIFE CICLE COSTS Axisymmetric approach and landing thrust reverser impacts on usage and LCC life cycle cost A82-40892 Logistics research program in the Onited states Air Force A82-40963 LIFT Kind-tunnel testing of 7/STOL configurations at high lift A82-40919 Minimum induced drag of canard configurations A82-41116 LIFT 10GBEBTATIOB Ejector powered propulsion and high lift subsonic wing A82-40970 Development of an advanced no-moving-parts high-lift airfoil A82-40971 Test results of chordwise and spanwise blowing for low-speed lift augmentation A82-40999 LIFT DBAG BA1IO Aerodynamic concepts for fuel-efficient transport aircraft A82-40957 A-31 LIGHT AIBCBAFI SUBJECT IHDBX LIGHT AIBCBAFI Sport aircraft Russian hook £82-40483 Computational and experimental studies of light twin aerodynamic interference A82-40930 Assessment of advanced technologies for high performance single-engine business airplanes A82-40932 The design integration of Hingtip devices for light general aviation aircraft A82-40933 LIGHT EHITTING DIODES Heads up display [8ASA-CASE-LAB-12630-1] , N82-29319 LIGHT TBABSHISSIOB Nearfield aerodynanics and optical propagation characteristics of a large-scale turret model [AD-A113910] N82-28624 LIGHTING ECOIPHEHI Effects of approach lijhting and variation in visible runway length on perception of approach angle in simulated night landings [AD-A114742] B82-29290 LIGHTHIHG A compendium of lightning effects on future aircraft electronic systems [AD-A114117J B82-28293 Carbon fiber reinforced ccnposite structures protected kith metal surfaces against lightning strike damage [MBB-OD-340-82-0/E] H82-28364 > Atmospheric electricity hazards analytical model development and application. Volume 1: Lightning environment modeling [AD-A114015] B82-29800 Atmospheric electricity Hazards analytical model development and application. Volume 2: Simulation of the lijutting/aircraft interaction event [AD-A114016] N82-29801 Atmospheric electricity hazards analytical model development and application. Volume 3: Electromagnetic coupling modeling of the lightning/aircraft interaction event [AD-A114017] S82-29802 LINEAB ABBAXS The design of a viewing system for near real time stereo images f r o m a QHA borne linescan sensor Unmanned Aircraft J82-39746 LINEAB SYSTEMS Application of multivariable model following method to flight controller [ A I A A PAPEB 82-1349] A82-39120 Applications to aeronautics of the theory of transformations cf nonlinear systems [HASA-TH-84249 ] B82-30013 LIHEABIZASIOH The use of linearized-aerodynamics and vortex-flow methods in aircraft design /invited paper/ [AIAA PAPEB 82-1384] A82-40294 LOAD TESTS On the bearing strengtns of CFBP laminates A82-39930 In-plane shear test of thin panels A82-40545 LOADS (FOBCES) Hind tunnel studies of store separation with load factor. Freedrops and captive trajectories H82-30261 LOGISTICS MANAGEMENT Logistics research program in the Dnited 'States Air Force A82-40963 LONGITUDINAL COSTEOL Design and analysis of d multivanable control system for a CCV-type fighter aircraft £ A I A A PAPEE 82-1350] A62-39121 Design of a longitudinal ride-control system by Zakian's method of inequalities A82-41114 Analytical and simulator study of advanced transport [NASA-CB-3572] B82-282S8 LONGITUDINAL STABILITY Hind tunnel measurements of longitudinal stability and control characteristics of primary and secondary wing configurations A82-41025 LOBAR C Flight evaluation of LOBAN-C in the State of Vermont [NASA-TH-84711] N82-28278 LOi 1BVBL TDBBOLEHCE The detection of low level wind shear. II A82-38463 LOi SPEED STABILITY Low-speed characteristics of a fighter-type configuration at high angles-of-attack and sideslip A82-41020 M BACH 10MBEB Flight-determined correction terms for angle of attack and sideslip [AIAA PAPEB 82-1374] A82-40290 HAGBBTIC COMPASSES Low cost development of INS sensors for expendable BPV control and navigation [AD-A112691] N82-28291 HAGBETIC SOBVEYS Geophysical flight line flying and flight path recovery utilizing the Litton LTN-76 inertial navigation system [DE82-005555] S82-29292 BAIHIENAICE Method for refurbishing and processing parachutes [NASS-CASE-KSC-11042-1] B82-29330 BAN BACBINE SYSTEMS A modern approach to pilot/vehicle analysis and the1 Heal-Snith criteria [AIAA PAPEB 82-1357] A82-39125 Evaluation of an automatic subsystem parameter monitor for aircraft A82-40552 Applying advanced technology to flight station design A82-40887 Human factors in air traffic control [AGABD-AG-275] S82-29293 Human factors contributions to air traffic control systems N82-29295 Man as a system component B82-29296 Human capabilities and limitations in systems B82-29297 Communications N82-29302 MABAGEMEBT SYSTEMS Future terminal area systems A82-38462 MANUAL COHTEOL The effects of the delays on systems subject to manual control A82-38943 Manual reversion flight control system for A-10 aircraft: Pilot performance and simulator cue effects [AD-A113463] B82-28302 BANOFACTUBIBG Development of materials and manufacturing technology over the next 20 years: Composite materials [MBB-UD-341-82-0] B82-28365 BATBBIAIS The development and applications of a full-scale wide body test article to study the behavior of interior materials during a postcrash fuel fire N82-29285 HATEBIALS TESTS Heat release rate calorimetry of engineering plastics A82-41075 MATHEMATICAL MODELS Aerodynamic behavior of a slender slot in a wind tunnel wall A82-38281 Pilot models for discrete maneuvers [AIAA 82-1519] A82-38940 Design of a longitudinal ride-control system by Zakian's method of inequalities A82-41114 Estimation of the number of in-flight aircraft on instrument flight rules A82-41117 A-32 SUBJECT IBD£Z BOOSTAIMS Beliability model for planetary gear [BASA-TH-82859] H82-28643 Establishment of a rotor model tasis [BASA-TP-2026] B82-29311 BAXIBOB LIKELIHOOD BS1IHA1BS Systen identification of nonlinear aerodynamic models H82-29996 HEASOBIHG IBSXBUHEHTS Primary-data devices Bussian book A82-39279 HBCHAHICAL PBOPEBTIES Technical and economic comparison of carbon fiber tape and woven fabric afplications A82-4C993 METAL BOHDING The promise of laminated metals in aircraft design A82-40903 HETAL FATIGUE Fatigue behavior of weldbonded joints 482-41115 HETAL HATHIX COHPOSITBS Application of a new hybrid material /ARAL!/ in aircraft structures A82-40975 HETAL SHBETS The promise of laminated metals in aircraft design A82-40903 HETAL SUBFACES Carbon fiber reinforcei composite structures protected with metal surfaces against lightning strike damage [HBB-UD-340-82-0/E] 882-28361 HBIEOBOLOGICAL £ADAB Demonstration of radar reflector detection and ground clutter suppression using airborne weather and mapping radar A82-U0532 HICBOBALABCES An evaluation of the fiosemcnnt ice detector for cloud water content neasurements [PB82-158833] B82-29321 MICEOCOMPDTEBS The detection of low level wind shear. II A82-38463 HICBOPBOCESSOBS Hydraulic Universal Display Processor System (HDDPS) [AD-A114428] H82-28294 HICBOUVE LAHDIBG SISTERS An MLS with computer aided landing approach [AIAA PAPEE 82-1352] A82-39122 BASA/FAA Helicopter ATC siiulation investigation of BBAV/HLE instrument approaches A82-10535 Flight simulation studies en the feasibility of laterally segmented approaches in an HLS environment A82-10941 Terminal area automatic navigation, guidance, and control research using the Microwave Landing System (HLS) . Part a: Transition path reconstruction alcng a straight line path containing a glideslope change waypoint [NASA-CB-3574-PT-4] H82-28269 HICB08AVE TBAHSHISSIOH The feasibility of a high-altitude aircraft platform with consideration of technological and societal constraints [BASA-TM-84508] B82-29313 HIDAIB COLLISIOHS Air-air collision avoidance systems A82-39323 Computer outages at air terminal facilities and their correlation to near miss mid-air collisions (AFMD-82-43) [B-20606U] B82-28264 KILITABI AIECHAFT JVX, what an opportunity -~ Joint Services Advanced Vertical Lift Aircraft Program A82-38423 Guidance for tbe use ox equivalent systems with HIL-F-8785C for aircraft flight control systems [AIAA PAPEE 82-1355] A82-39124 U.S. Army remotely piloted vehicle program A82-39732 Age exploration in naval aviation Beliability Centered Maintenance program A82-40962 Historical research and development inflation indices for Army fixed and rotor winged aircraft [AD-A114368] N82-28290 HILITABI AVIATIOH The national dynamics 'observer1 mini-BPV for tropical operation A82-3973U Age exploration in naval aviation Beliability Centered Maintenance program A82-40962 Logistics research program in the United States Air Force A82-10963 HILITABY BEIICOflEBS Flight dynamics of rotorcraft in steep high-g turns [AIAA PiPEB 82-1345] A82-39117 Recent advances in rotor technology at Boeing Vertol A82-40508 Whirl mode stability of the main rotor of the YAH-64 Advanced Attack Helicopter A82-40513 An evaluation of helicopter autorotation assist concepts A82-10524 Conceptual design of the LHX integrated cockpit A82-40527 The YAH-64 empennage and tail rotor - A technical history 482-10528 Concept demonstration of automatic subsystem parameter monitoring military helicopter cockpit instrumentation A82-40530 HIBIHUB DBAS Dual wing, swept forward swept rearward wing, and single wing design optimization for high performance business airplanes A82-10931 Hinimum induced drag of canard configurations A82-11116 HIBAGE AIBCBAFT Hirage 2000 - Towards possible high series production aircraft A82-38219 MISSILE COBFIGOBATIOHS Supersonic missile aerodynamic and performance relationships for low observables mission profiles [AIAA PAPEB 82-1298] A82-39085 Summary of sting interference effects for cone, missile, and aircraft configurations as determined by dynamic and static measurements [AIAA IAPEB 82-1366] A82-40395 HISSILE COBTBOL Air-to-air missile avoidance [AIAA 82-1516] A82-38939 Fixed pattern noise correction for staring arrays in guidance systems A82-39190 Algorithm development for infra-red air-to-air guidance systems A82-39191 HOISTDEE COHTEHT An evaluation of the Bosemount ice detector for cloud water content measurements [PB82-158833] H82-29321 flOBITOBS Evaluation of an autonatic subsystem parameter monitor for aircraft A82-10552 HOHOCLABES Dual wing, swept forward swept rearward wing, and single wing design optimization for high performance business airplanes A82-40931 HOKOPOLE AHTBHBAS Honopole antenna patterns on finite size composite ground planes m aircraft A82-11055 MOHTE CABLO HETHOD Digital computer simulation of modern aeronautical digital communication systems A82-10910 BOBTALITI Human response to fire N82-29281 HODHTAIBS Flight evaluation of LOEAN-C in the State of Vermont [NASA-TH-81711] N82-28278 A-33 HOVIBG TiBSEI IBDIC4TOBS SUBJECT IIDBZ S82-29520 flOVIHG T4BGET ISDICATOES Moving target detector (Hod 2) [AD-4114709] HHCA AIBCBAFT Engineering aspects of international collaboration on Tornado 482-10878 BOLTIEHOCBSSIBG (COHP01KBS) The design of a BPV ground 'station simulator 482-39750 N NACELLES Aerodynamic characteristics of a large-scale, twin tilt-nacelle V/STOL aodel [4144 PAPEB 81-0150] 482-38143 H4S4 PB06BAHS Summary and recent results from the NASA advanced high-speed propeller research program [4144 P4PEB 82-1119] 482-40419 Predesign study for an advanced flight research rotor 482-40525 Flight test evaluation of a video tracker for enhanced offshore airborne radar approach capability 482-40531 NAS4 research on viscous drag reduction 482-40896 HiTIOHAL AIBSPACE UIU.IZA1IOH SYSTEM Estimation of the peak count of actively controlled aircraft 482-38447 BAVIGAIIOB AIDS Problems in the simulation of correlation-extremal navigation sjsteas 482-39403 Simulation of correlation-extremal receivers of signals frcm samflinj-phase radio-navigation systems 482-39404 General aviation activity and avionics survey [AD-A112924] H82-28244 flight evaluation of LOBAN-C in the State of Vermont [HAS4-TM-84711] S82-28278 HBTSOBK ANALYSIS System data communication structures for active-contrcl transport aircraft, volume 1 [NAS4-CB-165773-VOL-1] 1182-29510 HETBOBK SIHTBESIS flight contrcl synthesis ising robust output observers [(414482-1575] 482-39016 BOISE INTENSITY Field studies of the Air force procedures (NOISECHECK) for aeasuring community noise exposure from aircraft operations [4D-4113672] H82-28841 BOISE HBASOBEBEB* Field studies of the Air Force procedures (NOISECHECK) for measuring community noise exposure f rom aircrart operations [AD-4113672] K82-28841 Use of the cavitation tunnel at the Dutch Naval Experiment station ( D S P ) , Nageningen for the determination of the acoustic source strength of propeller cavitation [TPD-908-720] N82-29116 Estimated airplane noise levels in A-weighed decibels [4C-36-3B] N82-30029 Forward velocity effects en fan noise and the suppression characteristics of advanced inlets as measured in the NASA-Ames 40 by 80 foot wind • tunnel [H4SA-CB-152328] H82-30030 OS4F bioenvironmental noise data handbook. Volume 148. T-37B in-flight crew noise [4D-4114943] H82-30031 Far-field acoustic data for the Texas ASE, Inc. hush house [AD-4114564] N82-30032 BOISB POLLOTIOB Hoise pollution and airport regulation 482-40051 O'Bare International Airport - Impervious to proposed state efforts tc licit airport noise 482-40052 BOISE PBEDICTIOH (AIBCBAFT) The prediction of helicopter rotor discrete freguency ncise A82-40553 A semiempirical high-speed rotor noise prediction technique 482-40554 Dynamic surface measurements on a model helicopter rotor during blade slap at high angles of attack 482-40555 Some comments on the prediction of forward flight effects on jet noise [HPIS-20/1981] N82-29118 BOISE BBDOCTIOB Fixed pattern noise correction for staring arrays in guidance systems 482-39190 NASA research in supersonic propulsion - A decade of progress [4144 PAPEB 82-1048] 482-40417 Predesign study for an advanced flight research rotor A82-40525 Demonstration of radar reflector detection and ground clutter suppression using airborne weather and mapping radar 482-40532 Static noise tests on modified augmentor wing jet STCL research aircraft [NASA-TM-81231] H82-28295 The effect of barriers on wave propagation phenomena: Kith application for aircraft noise shielding [HASA-CB-169128] N82-29111 The cost of noise reduction for departure and arrival operations of commercial tilt rotor aircraft [NASA-CB-137803] 882-29316 BOMOGBAPHS Computer enhanced analysis of a jet in a cross-stream N82-29555 BOBDZSTBDCTIVE TESTS Nondestructive testing in aircraft construction using holographic methods A82-40977 Beccmmended practice for a demonstration of Nondestructive Evaluation /BDE/ reliability on aircraft production parts - Introduction to the guidelines A82-41140 BOBLIBBAB EQUATIONS The rectangular wing with semiinfinite span in nonlinear theory A82-39359 BOB1IIBAB SYSTEMS An analysis of a nonlinear instability in the implementation of a VTOL control system during hover [4144 82-1611] 482-38990 The determination of gust loads on nonlinear aircraft using a power spectral density approach [BLE-TB-80123-0] N82-28303 System identification of nonlinear aerodynamic models N82-29996 Applications to aeronautics of the theory of transformations of nonlinear systems [B4S4-TB-84249] N82-30013 BOSB TIPS Analysis and wind tunnel tests of a probe used to sense altitude through measurement of static pressure [4IAA P4PEB 82-1361] 482-39128 HOZZLE FLOi An improved propulsion system simulation technique for scaled wind tunnel model testing of advanced fighters 482-41019 BOSSLE 6ECMBTBY 4 summary of V/STOL inlet analysis methods [NASA-1H-82S85] B82-28249 BOCLEAB PEOPOLSICI The feasibility of a high-altitude aircraft platform with consideration of technological and societal constraints [BASA-Tfl-84508] K82-29313 4-34 SOBJECT IBDEI PASSBBGEE AIRCRAFT NUMERICAL ANALYSIS Numerical methods for solving boundary value problems for noncavitating and cavitating flow past King profiles A82-38722 NUMERICAL COHTEOL Design and flight testing of digital direct side-force ccntrcl lavs [AIAA 82-1521] A82-38941 Digital full authority controls for helicopter engines A 82- 4 0522 Design and flight testing of a digital optimal control general aviation autopilot 482-40906 Advanced aircraft electrical system control technology demonstrator. Phase 1: Analysis and preliminary design [AD-A113633] N82-28284 OBLIflOB ilKGS Dnique flight characteristics of the AD-1 oblique-wing research airplane [AISA PAPEE 82-1329] 482-39106 OBSEBVABI1ITI (STSTEHS) Flight contrcl synthesis tsing robust output observers [ (AIAA 82-1575] A82-39016 OHBOABD DATA PROCESSING A preliminary laboratory evaluation of a reconfigurable integrated flight control concept [AIAA 82-15S7] A82-38982 Investigations concerned with shifting pilot activities tc a higher hierarchical stage of flight control Garman thesis A82-41453 OSBOABD EO.OIPMEHT Feasibility study of a 270V dc flat cable aircraft electrical pover distributed system [AD-A114026] H82-28552 OPERATING COSTS Minimization of the total costs incurred in the employment of passenger jet aircraft A82-39247 Advanced technologies applied to reduce the operating costs cf small commuter transport aircraft A32-40915 OPTICAL EQUIPMENT Design study for a low-distortion holographic HUD [AD-A113982] 1182-28292 OPTICAL RADAR Radars for UBA A82-39742 Baseline monitoring using aircraft laser ranging spaceborne laser simulation and aircraft laser tracking [NASA-TB-73298] S82-28690 OPTICAL SCANNERS Application of an optical data link in the airborne scanning system A82-39275 Opto-electronical push-croon scanners for navigation, reconnaissance and generation of digital data bases A82-39747 OPTIHAL CONTBOL Bobust Kalman filter design for active flutter suppression systems A 82-38442 Parameter estimation applied to general aviation aircraft - A case study [AIAA PAPEE 82-1^13] A82-39094 Optimal three-dimensional turning performance of supersonic aircraft [AIAA PAPfiB 82-1^26] A82-39103 A modern approach to pilot/vehicle analysis and the Heal-Smth criteria [AIAA PAPEB 82-1357] A82-39125 Optimal control application in supersonic aircraft performance A82-39374 Design and flight testing of a digital optimal control general aviation autopilot A82-40906 Optimal open-loop aircraft control for go-around maneuvers under Hind shear influence A82-40943 Analytical and simulator study of advanced transport [NASA-CB-3572] N82-28298 OPTIMISATION Efficient optimum design of structures - Program DDDO A82-38146 Application of the sequential optimization method to the tuning of the natural frequencies of gas-turbine engine compressor blades A82-39399 Optimum structural design for helicopters A82-40543 Optimizing aerospace structures for manufacturing cost A82-41014 Optimization of canard configurations - An integrated approach and practical drag estimation method A82-41023 CEBIT DECAI (relaunch estimates of near Earth satellite lifetimes using quasi-dynamic atmosphere models - application to a proposed Brazilian satellite [IHJE-2325-PRB/080] N82-29347 OSCILLATION DAHPEBS Theoretical and experimental investigation 'of joint-structural damping interaction for airplane construction A82-41013 OZONE Tvo-dimensional model studies of the impact of aircraft exhaust emissions on tropospheric ozone A82-40124 PANEL METBOD (FLUID DINAfllCS) Lateral aerodynamics of delta wings with leading edge separation [AIAA PAPEB 82-1386] A82-39142 PABELS Design and fabrication of cocured composite hat-stiffened panels A82-40978 PABACHOTE FABRICS Method for refurbishing and processing parachutes [SASA-CASE-KSC-11042-1] 882-29330 PABACHOTES Method for refurbishing and processing parachutes [SASA-CASE-KSC-11042-1] N82-29330 PARALLEL FLOW The unsteady motion of a wing traveling at subsonic speed above a plane A 82-39358 PARAMETER IDENTIFICATION A recursive terrain height correlation system using multiple model estimation techniques [AIAA 82-1513] A82-38937 Applications of parameter estimation in the study of spinning airplanes [AIAA PAPEB 82-1309] A82-39090 A simple, low cost application of a flight test parameter identification system [AIAA PAPEB 82-1312] A82-39093 Parameter estimation applied to general aviation aircraft - A case study [AIAA PAPEB 82-1313] A82-39094 NASA Dryden's experience in parameter estimation and its uses in flight test [AIAA PAPEB 82-1373] A82-39135 Determination of airplane aerodynamic parameters from flight data at high angles of attack A82-40928 System identification of nonlinear aerodynamic models B82-29996 PASSENGER AIBCBAPT Minimization of the total costs incurred in the employment of passenger jet aircraft A82-39247 Optimized 10 ton class commercial aircraft engine A82-40890 Advanced technologies applied to reduce the operating costs of snail comauter transport aircraft A82-40915 1-35 PATTEBB BEGJSTE1TIOH SDBJECT IHDEX PATTBBS BEGISIBATIOH Scanner imaging systems, aircraft 882-28715 PEHDOLDHS Helicopter vibration suppression using simple pendulum absorbers on the rotor Hade [NASA-CB-169131] M82-28282 PBBFOBHAHCE PBBDICTIOB An alternate method of specifying handwidth for flying qualities f ( A I A A 82-1609] A82-38988 Supersonic missile aerodynamic and performance relationships for Ion observables mission profiles [AIAA PAPEB 82-1298] A82-39085 The correlation of flijnt test and analytic H-on-N air coaiat exchange ratios Many-on-Hany [AIAA PAPEB 82-1328] A82-39105 Analysis of an airflana windshield anti-icing systea [ A I A A PAPEB 82-1372] A82-39134 Analytic extrapolation to full scale aircraft dynamics [AIAA PAPEE 82-1387] A82-39113 An experimental investigation of a bearingless model rotor in hover A82-40512 Correlation of predicted vitrations and test data for a wind tunnel helicopter model A82-U0515 Digital computer simulation of modern aeronautical digital communication systems A82-U0940 The prediction of propeller/wing interaction effects A82-U09U8 Development of the Circulation Control sing-Upper Surface Blowing poweied-lift system for SIOL aircraft A82-40969 PEBFOBBiHCE TESTS Performance of the Botor Systems Besearch Aircraft calibrated rotor loads measurement system 482-40549 PEBSOHHEL Additional functions within the air traffic control system B82-29309 PHOTOCHEBICAL BEACTIOSS Two-dimensional model studies of the impact of aircraft exhaust emissions on tropospheric ozone A82-40124 PHOTOGBAPHIC PLATES High-sensitivity holographic plates IL-3H A82-41575 PILOT PBBPOBHAHCB Pilot models for discrete maneuvers [AIAA 82-1519] ' A82-38940 Ihe effects of the delays en systems subject to manual contrcl A82-38943 The ideal controlled element for real airplanes is not K/s [ A I A A 82-1606] 482-38986 A modern approach to pilot/vehicle analysis and the Seal-Smith criteria [ A I A A PAPEB 82-1357] A82-39125 The system of 'objective control* A82-39245 Manual reversion flight control system for A-10 aircraft: Pilot performance and simulator cue effects [AD-A113463] N82-28302 PILOI TBAIBIBG Visual scene.simulation concerning the landing of sporting aircraft in connection Kith investigations regarding the control and learning behavior of the pilot German thesis A82-U14M7 PILOTLESS AIBCBAFT BACHAB - A unmanned aircraft flight research facility A82-39735 PITCaiBS BOHEBTS Development and flight test evaluation of a pitch stability augmentation system for a relaxed stability 1-1011 [AIAA PAPEB 82-1297] A82-39084 Kind tunnel measurements of longitudinal stability and control characteristics of primary and secondary wing configurations A82-41025 FITOT TDEES Correlation of Preston-tube data with laminar skin friction (Log No. J12984) [NASA-TH-84827] H82-29556 FLAIE SIBAID In-plane shear test of thin panels A82-40545 PLABillG Hunan factors contributions to air traffic control systems N82-29295 PLASHi AGC iELDIBG In-motion radiography of titanium spar tube welds A82-40538 ELASTIC AIBCBAFT SIBOCTOBES Development of the advanced composite ground spoiler for c-1 medium transport aircraft A82-3989S Development status of a composite vertical stabilizer for a jet trainer A82-39897 Operation ¥10! - Development of a composite material wing A82-10934 Development of materials and manufacturing technology over the next 20 years: Composite materials [UBB-UD-341-82-0] H82-28365 PLASTICS Heat release rate calorimetry of engineering plastics A82-41075 FLOTTEBS Programs for the transonic wind tunnel data processing installation. Part 8: Programs for processing data on the central site computer [AD-A112900] N82-28310 EOLIHEBIZATIOB Hater-compatible polymer concrete materials for use in rapid repair systems for airport runways [DE82-010994] N82-29464 POBOOS BOOHDABZ LAIEB COBTBOL Aerodynamic development of laminar flow control on swept wings using distributed suction through porous surfaces A82-40894 POBOOS PLATES Turbulent boundary layer on a porous surface with infection at various angles to the wall A82-39K82 FOTEBTIA1 FLO! Evaluation of an asymptotic method for helicopter rotor airloads A82-U0509 Transonic small disturbance code for body-wing configuration coupled with full potential code for wing alone A82-40899 The prediction of propeller/wing interaction effects A82-40948 FOBDEB HETALLOBGI International aviation (selected articles) [AD-A114422] B82-28245 POilEBED LIFT AIBCBAFT Development of the Circulation Control King-Upper Surface Blowing powered-lift system for STOL aircraft A82-40969 Ejector powered propulsion and high lift subsonic wing A82-40970 QCSEE over-the-wing engine acoustic data [NASA-Ifl-82708] N82-29324 PBEDICTIOS ABALISIS 1ECHHIQOES Prediction of fatigue crack growth rates under variable loading using a simple crack closure model [DLE-I1P-81023-U] B82-28685 Effect of water on axial flow compressors. Part 2: Computational program [iD-A111831] H82-29327 PBEDIC1IOBS Future trends and problems H82-29310 PBESSDBE DISTBIBDTIOB Experimental and theoretical studies of three-dimensional turbulent boundary layers on an empennage of a typical transport airplane A82-40955 A-36 SUBJECT IHDIJC B4DAB TABGEIS PBESSDEE GBiDIEHTS Comparison of experimental and analytic performance for contoured endwall stators [4144 PSPEE 82-1286] 482-40422 PHESSUBE HEASUBEHBBT analysis and wind tunnel tests of a probe used to sense altitude throujn measurement of static pressure [4144 PAPES 82-1361] 482-39128 An experimental investigation of leading-edge spanwise bloving 482-40988 PBESSUBE SEHSOBS Analysis and wind tunnel tests of a probe used to sense altitude through zeasurement of static pressure [4IA4 P4PEE 82-1361] 482-39128 PBE?EH1IOH Hunan response to fire N82-29281 PBOBABILITI TBEOBS The Shiryayev sequential probability ratio test for redundancy management [4144 82-1623] 462-38998 PBODDCTIOI COSIS Unmanned aircraft in f u t u r e combat 482-39728 PBOJECI H4JAGEHEBI Engineering aspects of international collaboration on Tornado 482-10878 PBOPELLEB BLAEBS The application of snail propellers to BPV propulsion 482-39737 PBOPELLEB PAHS Turboprop design - Sou and the future 482-1(0965 PBOPELLEB SLIPS1BI4HS The prediction of propeller/wing interaction effects 482-10948 Use of the cavitation tunnel at the Dutch Naval Experiment station (iSP), Hageningec for the determination of the acoustic source strength of propeller cavitation [TPD-908-720] N82-29116 PBOPELLEBS Propulsion opportunities for future coanuter aircraft [4144 P4PEB 82-1C49] 482-40418 Summary and recent results from the BSSA advanced high-speed propeller research program [4144 P4PEB 82-1119] 482-40419 Use of the cavitation tunnel at the Dutch Naval Experiment station (H3P), Hageningen for the determination of the acoustic source strength of propeller cavitation [TPD-908-720] N82-29116 Beads up display [8ASA-CASE-IAB-12630-1 ] N82-29319 PBOPOLSIOB SISIEH COHHGOBAUCBS Evaluation of an experimental technique to investigate the effects cf the engine position on engine/pylon/King interference Bind tunnel tests [HLS-HP-81020-U] H82-28262 PBOPOLSICB SISTIH PEBPOBHAHCI Supersonic missile aerodynamic and performance relationships for lo« observables uission profiles [4144 PAPEB 82-1298] 482-39085 Hini-EPV propulsion 482-39736 The application of small propellers to BPV propulsion 482-39737 Electric propulsion for a iini EPV system 482-39744 Propulsion opportunities for future commuter aircraft [4144 P4PEE 82-1049] 482-40418 Summary and recent results from the NASA advanced high-speed propeller research program [4144 PAPEB 82-1119] 482-40419 Civil helicopter propulsion system reliability and engine monitoring technology assessments 482-40518 4erodynamic concepts for fuel-efficient transport • aircraft 482-40957 An improved propulsion system simulation technique for scaled Kind tunnel model testing of advanced fighters 482-41019 PBOPUISIVE EFFICIENCY The application of small propellers to BPV propulsion ' 482-39737 4ircraft design for fuel efficiency 482-40973 PBOTECT10B Carbon fiber reinforced composite structures protected with metal surfaces against lightning striJse damage [HBB-UD-340-82-0/E] N82-28364 EBOTECIIVE CLOTHING Human response to fire N82-29281 PBOTOTYPES Evaluation of CFBP prototype structures for aircraft 482-39892 Fabrication of CFEP prototype structure for aircraft horizontal tail leading edge slat rail 482-39896 PULSE COBHUNICATION Digital computer simulation of modern aeronautical digital communication systems 482-40940 POLIBDSIOH Adaptation of pnltrusion to the manufacture of helicopter components 482-40537 PUSHBBOOB SEBSOB HOPES Opto-electronical push-broom scanners for navigation, reconnaissance and generation of digital data cases 482-39747 SOADBATIC PBOGBABHIBG Efficient optimum design of structures - Program DDDO A82-38146 QU4LIII CCHIBOL Eecommended practice for a demonstration of Nondestructive Evaluation /NDE/ reliability on aircraft production parts - Introduction to the guidelines A82-41140 R BAD4B DETECTION Complete flexibility and realism in radar simulation 482-38461 Demonstration of radar reflector detection and ground clutter suppression using airborne Heather and mapping radar A82-40532 BADAB EQDIEMEHT Badars for DMA 4B2-39742 BADAE B4ES Demonstration of radar reflector detection and ground clutter suppression using airborne weather and mapping radar 482-40532 S4D4B HEASOEEHENT Baseline monitoring using aircraft laser ranging spaceborne laser simulation and aircraft laser tracking [BASA-TM-73298] M82-28690 BADAB BEFLEC10BS Demonstration of radar reflector detection and ground clutter suppression using airborne weather and mapping radar A82-40532 BADAB BESOLOTIOH Flight test evaluation of a video tracker for enhanced offshore airborne radar approach capability 482-40531 BADAB TABGETS (loving target detector (Hod 2) [AD-4114709] N82-29520 4-37 BiDiB TBACKIBG SDBJECT IHDBX BAD4B TBACKIHG Analysis of general-aviation accidents using 4TC radar records [4144 P1PEB 82-1310] 482-39091 Target tracking using area correlation AS2-39194 Flight test evaluation of a video tracker for enhanced offshore airnorne radar approach capability 482-40531 Besearch on an adaptive Kalman filter for solving the radar tracking problem German thesis 482-40562 B1DI4I PIC! Calculation of level flow using radial grating , 482-38922 Cooled variable nozzle radial turbine for rotor craft applications [H4S4-CB-165397] B82-29323 BADIO ATIEBUATIOH Electronagnetic Propagation Probleus in the Tactical Environment [AGABD-LS-120] N82-29527 RADIO BEACOBS Minimum operational perfornance standards for automatic direction finding (ADF) equipment [BTC4/DO-179] H82-28270 BADIO COBH0BIC11IOB Propagation problems associated with aircraft communications systeas H82-29535 BADIO DIBECTIOM FIHDBBS Minimum operational performance standards for automatic direction finding n fan noise and the suppression characteristics of advanced inlets as measured in the NASA-Ames 40 by 80 foot wind tunnel [NASA-Cfi-152328] 1182-30030 UTAH OB ALLOIS The technological aspects cf titaniuo application in the TO-144 aircraft structure A82-39718 In-motion radiography of titanium spar tube welds A82-40538 International aviation (selected articles) [AD-A114422] 1182-28245 TOLEBAHCES (BECfiAHICS) Computer aided coordinate measuring systems in engineering design of helicopter components A82-40540 Multistage axial compressor program en tip clearance effects [AD-A107445] N82-29325 TOBSION Flap-lag-torsional dynamics of extensional and inextensional rotor Blades in hover and in forward flight [H1SA-CB-169159] H82-29312 TOBED BODIES Maneuver stability of a vehicle with a toned body [AIAA PAPEB 82-1347] A82-39119 TBACKIHG PBOB1EH Target tracking using area correlation 682-39194 Besearch on an adaptive Kalman filter for solving the radar tracking problem German thesis A82-40562 IBAILHG EDGES Inflated wings A82-40966 Development of an advanced no-moving-parts high-lift airfoil A82-40971 TBAILIHG-BDGB FLAPS * Investigation of the unsteady airloads on a transport aircraft tjpe airfoil with two interchangeable oscillating trailing edge flaps, at transonic speed and high Beynclds numbers A82-40909 Determination of the efficiency of a trailing edge flap in unsteady three-dimensional flow A82-40910 1BAIHIIG AIBCBAFT Development status of a composite vertical stabilizer for a jet trainer A82-39897 Spin behaviour of the Pilatus PC-7 Turbor Trainer A82-40979 A discussion of the flying quality requirements of a rasic training aircraft [AD-A114805] 1182-29318 SBAIHIHG AHALISIS Operational test and evaluation handbook for aircraft training devices. Volume 1: Planning and management [AD-A112498] 1182-29332 TBAIBIHG DEVICES Smoke abatement system for crash rescue/fire training facilities [AD-A114380] H82-28268 IBAIBIHG BVALOATIOH Operational test and evaluation handbook for aircrew training devices. Volume 3: Operational suitability evaluation [AD-A112569] 1182-28306 Operational test and evaluation handbook for aircraft training devices. Volume 1: Planning and management [AD-A112498] S82-29332 TBAIBISG SIHOLATOBS Complete flexibility and realism in radar simulation A82-38461 TRAJECTOBIES Hind tunnel studies of store separation with load factor, Freedrops and captive trajectories H82-30261 TBAJECTOEI ASALISIS Dser's manual for the AHEEB flight path-trajectory simulation code [DE82-007004] 1182-29343 TBABSFEB FOBCTIOIS The ideal controlled element for real airplanes is not K/s [AIAA 82-1606] A82-38986 Investigation of low order lateral directional transfer function models for augmented aircraft [AIAA 82-1610] A82-38989 The effects of atmospheric turbulence on a guadrotor heavy lift airship [AIAA 82-1542] A82-39009 TEABSFOBBATIOBS (BATHEBATICS) Applications to aeronautics of the theory of transformations of nonlinear systems [MASA-Tfl-84249] B82-30013 TBABSBISSIOH Advances in high-speed rolling-element bearings [BASA-TB-82910] 1182-28644 TBABSfllSSIOB LUES Feasibility study of a 270V dc flat cable aircraft electrical power distributed system [AD-A114026] D82-28552 1BAHSBISSIOBS (BACfllBE ELEBEHTS) Reliability aodel for planetary gear [HJSi-TB-82859] B82-28643 TEAHSOBIC FLIGHT Ring design for supersonic cruise/transonic maneuver aircraft A82-41021 TBABSOSIC F10B numerical solution of a problea concerning transonic flow past a wing-fuselage configuration A82-39996 A nev Transonic Airfoil Design Bethod and its application to helicopter rotor airfoil design A82-40507 Calculations of transonic steady state aeroelastic effects for a canard airplane A82-40882 Viscous transonic airfoil flow simulation A82-40897 Transonic small disturbance code for body-wing configuration coupled with full potential code for wing alone A82-40899 A finite difference method for the calculation of transonic flow about a wing, based on small perturbation theory [HLB-TB-81031-0] H82-28263 A-46 SUBJECT INDEX TUBBOJET ENGIIES TBAHSONIC BIND TOHHEIS Aerodynamic behavior or a slender slot in a wind tunnel Hall 482-38281 Estimation of simulation errors in the European Transonic Hind Tunnei /E1H/ A82-40950 National Transonic facility (NTJ) prototype fan blade fatigue test [AD-A114405] B82-28261 Programs for the transonic wind tunnel data processing installation. Part 8: Programs for processing data on the central site computer [AD-A112900] N82-28310 Design basis for a new transonic Hind tunnel [AD-A112899] N82-28311 Hindtunnel capability related to test sections, cryogenics, and computer-windtunnel integration [AGAJ3D-AB-174] N82-29334 Correlation of Preston-tube data with laminar skin friction (Log No. J12984) [BASA-TH-84827] H82-29556 TBABSPOB1 AlfiCBAPT Investigation of the unsteady airloads on a transport aircraft t jpe airfoil with tno interchangeable oscillating trailing edge flaps, at transonic speed and high Reynolds numbers A82-40909 A concept for 4E-\) H - V C I L I T V - . 'A* / V C C E S S I O . J I Jo r> 0 dOX 8 757 ! I 21240 National Aaronaulcs and Spac* AdminisiralKX) NASA-4SI O«ioal Business Penally lor Private Use $300 NASA POSTMASTER: If Undclivcrablc (Section 158 Postal Manual) Do Not Return

Aeronautical Engineering: A continuing bibliography with indexes, supplement 154

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