Aeronautical Engineering: A special bibliography with indexes, supplement 64, December 1975

This bibliography lists 288 reports, articles, and other documents introduced into the NASA scientific and technical information system in November 1975

The 15th Aerospace Mechanisms Symposium

Technological areas covered include: aerospace propulsion; aerodynamic devices; crew safety; space vehicle control; spacecraft deployment, positioning, and pointing; deployable antennas/reflectors; and large space structures. Devices for payload deployment, payload retention, and crew extravehicular activities on the space shuttle orbiter are also described

Certification Considerations for Adaptive Systems

Advanced capabilities planned for the next generation of aircraft, including those that will operate within the Next Generation Air Transportation System (NextGen), will necessarily include complex new algorithms and non-traditional software elements. These aircraft will likely incorporate adaptive control algorithms that will provide enhanced safety, autonomy, and robustness during adverse conditions. Unmanned aircraft will operate alongside manned aircraft in the National Airspace (NAS), with intelligent software performing the high-level decision-making functions normally performed by human pilots. Even human-piloted aircraft will necessarily include more autonomy. However, there are serious barriers to the deployment of new capabilities, especially for those based upon software including adaptive control (AC) and artificial intelligence (AI) algorithms. Current civil aviation certification processes are based on the idea that the correct behavior of a system must be completely specified and verified prior to operation. This report by Rockwell Collins and SIFT documents our comprehensive study of the state of the art in intelligent and adaptive algorithms for the civil aviation domain, categorizing the approaches used and identifying gaps and challenges associated with certification of each approach

Design & modelling of a composite rudderless aeroelastic fin structure

This thesis presents the study of a gapless and rudderless aeroelastic fin (GRAF) to enhance the directional stability and controllability of an aircraft. The GRAF concept was proposed and developed in the wake of previous research, targeted to improve flight performance and manoeuvrability, and to reduce fuel consumption and airframe weight. The study involved the subjects of aerodynamics, structural design and analysis, and flight mechanics. The work includes conceptual design, structural modelling, aeroelastic analysis and flight performance evaluation of a GRAF variant designed for a small subsonic Unmanned Aerial Vehicle (UAV). The Eclipse UAV, a platform designed by part time students at the Department of Aerospace Engineering of Cranfield University, was chosen as a case study. A new approach to design a more effective fin with an unconventional structural layout and novel techniques which have not been investigated in previous research is proposed. Despite the GRAF planform being similar to classical fin-hinged rudder configurations, it is provided with a flexible gapless control surface, kept as one continuous piece and integrated with the fin primary structure. With its fixed root and rudderless feature, the GRAF adopts an original method of operation. Its way of working relies upon an unconventional technique of combining morphing technology and aeroelastic effect. The morphable configuration is twisted to gain an aeroelastically beneficial effect to enhance the efficiency and manoeuvrability of the aircraft. This warping capability of the fin is the key role player enabling the GRAF surface to seamlessly generate the required aerodynamic forces. Unlike the conventional structures designed to be as rigid as possible to withstand the external loads, the GRAF will exploit its structure‟s flexibility to use the aeroelastically induced twist deformations for a self-adaptive warping behaviour and improve flight dynamic response and performance. In order to ensure the above features are achievable in practice, further study on the structural configuration was conducted. To achieve performance improvement, together with the original structural layout and aeroelastic effect exploitation, another three novel key components are investigated, proposed and introduced in the GRAF model. A structurally integrated actuation system, termed L-shape stringers device (LSS), is designed to transform actuator axial forces in spanwise distributed bending moments, to create seamless deformations of the trailing edge (TE) section. An innovative trailing edge joint, namely the swivel edge closure, is specifically designed to enhance the mobility and degrees of freedom of the trailing edge box. It is a revolutionary concept which, by virtually interrupting the structural integrity of the closed TE section, allows relative translation and rotation of the TE panels. Finally, it is the novel concept of the slot-connection that, whilst appearing to clamp the GRAF structure inside the slot, actually enables the design to increase the twist angle at the tip of the fin without overstressing the materials. In order to enhance the GRAF efficiency, a tailored design of the fin structure was conducted. A novel internal structure configuration integrated with the key components has been designed to be connected to a flexible cladding skin, rotating ribs and a load-carrying tubular beam all of which constitute the primary parts of the GRAF model. With the ultimate goal of a lighter tail version, the entire design has been made by using composite, light frames, in an engineering trade-off of stiffness, elasticity, weight and cost of both glass and carbon fibre laminates. The analysis via 2-D aerodynamic codes and FEA was conducted to assess and validate the GRAF model and the obtained performance. Static linear elastic analysis has been carried out to verify the structural layout of the novel design subject to strength and stiffness criteria in addition to the fin warping and cambering capabilities. Also an investigation of aeroelastic stability related to steady and unsteady aerodynamic conditions has been carried out during the model analysis phase. The study has shown that although the GRAF divergence and flutter margins are slightly smaller than those of the conventional fin, the design and performance requirements are satisfied within the very challenging objective of a lighter vertical tail structure.The dynamic analysis study has also demonstrated the beneficial effect obtained by damping yawing oscillations when such a self-adaptive structure, compared to a rigid one, can be operated under cross wind circumstances. The manufacturing feasibility and assembly of the GRAF structure has been explored with the construction of a 1:1 scale model of the fin prototype. The model has been used as concept demonstrator to assess the functionality of the introduced technical novelties, the ease of manufacturing and the structural weight of the final assembly.EThOS - Electronic Theses Online ServiceGBUnited Kingdo

Social work with airports passengers

Social work at the airport is in to offer to passengers social services. The main methodological position is that people are under stress, which characterized by a particular set of characteristics in appearance and behavior. In such circumstances passenger attracts in his actions some attention. Only person whom he trusts can help him with the documents or psychologically

Standardization Roadmap for Unmanned Aircraft Systems, Version 2.0

This Standardization Roadmap for Unmanned Aircraft Systems, Version 2.0 (“roadmap”) is an update to version 1.0 of this document published in December 2018. It identifies existing standards and standards in development, assesses gaps, and makes recommendations for priority areas where there is a perceived need for additional standardization and/or pre-standardization R&D. The roadmap has examined 78 issue areas, identified a total of 71 open gaps and corresponding recommendations across the topical areas of airworthiness; flight operations (both general concerns and application-specific ones including critical infrastructure inspections, commercial services, and public safety operations); and personnel training, qualifications, and certification. Of that total, 47 gaps/recommendations have been identified as high priority, 21 as medium priority, and 3 as low priority. A “gap” means no published standard or specification exists that covers the particular issue in question. In 53 cases, additional R&D is needed. As with the earlier version of this document, the hope is that the roadmap will be broadly adopted by the standards community and that it will facilitate a more coherent and coordinated approach to the future development of standards for UAS. To that end, it is envisioned that the roadmap will continue to be promoted in the coming year. It is also envisioned that a mechanism may be established to assess progress on its implementation

12th EASN International Conference on "Innovation in Aviation & Space for opening New Horizons"

Epoxy resins show a combination of thermal stability, good mechanical performance, and durability, which make these materials suitable for many applications in the Aerospace industry. Different types of curing agents can be utilized for curing epoxy systems. The use of aliphatic amines as curing agent is preferable over the toxic aromatic ones, though their incorporation increases the flammability of the resin. Recently, we have developed different hybrid strategies, where the sol-gel technique has been exploited in combination with two DOPO-based flame retardants and other synergists or the use of humic acid and ammonium polyphosphate to achieve non-dripping V-0 classification in UL 94 vertical flame spread tests, with low phosphorous loadings (e.g., 1-2 wt%). These strategies improved the flame retardancy of the epoxy matrix, without any detrimental impact on the mechanical and thermal properties of the composites. Finally, the formation of a hybrid silica-epoxy network accounted for the establishment of tailored interphases, due to a better dispersion of more polar additives in the hydrophobic resin

33rd Aerospace Mechanisms Symposium

The proceedings of the 33rd Aerospace Mechanisms Symposium are reported. JPL hosted the conference, which was held at the Pasadena Conference and Exhibition Center, Pasadena, California, on May 19-21, 1999. Lockheed Martin Missiles and Space cosponsored the symposium. Technology areas covered include bearings and tribology; pointing, solar array and deployment mechanisms; orbiter/space station; and other mechanisms for spacecraft