Orbiter Flying Qualities (OFQ) Workstation user's guide

This project was devoted to the development of a software package, called the Orbiter Flying Qualities (OFQ) Workstation, for working with the OFQ Archives which are specially selected sets of space shuttle entry flight data relevant to flight control and flying qualities. The basic approach to creation of the workstation software was to federate and extend commercial software products to create a low cost package that operates on personal computers. Provision was made to link the workstation to large computers, but the OFQ Archive files were also converted to personal computer diskettes and can be stored on workstation hard disk drives. The primary element of the workstation developed in the project is the Interactive Data Handler (IDH) which allows the user to select data subsets from the archives and pass them to specialized analysis programs. The IDH was developed as an application in a relational database management system product. The specialized analysis programs linked to the workstation include a spreadsheet program, FREDA for spectral analysis, MFP for frequency domain system identification, and NIPIP for pilot-vehicle system parameter identification. The workstation also includes capability for ensemble analysis over groups of missions

Cryogenic Optical Performance of a Lightweighted Mirror Assembly for Future Space Astronomical Telescopes: Correlating Optical Test Results and Thermal Optical Model

A 43cm diameter stacked core mirror demonstrator was interferometrically tested at room temperature down to 250 degrees Kelvin for thermal deformation. The 2.5m radius of curvature spherical mirror assembly was constructed by low temperature fusing three abrasive waterjet core sections between two CNC pocket milled face sheets. The 93% lightweighted Corning ULE mirror assembly represents the current state of the art for future UV, optical, near IR space telescopes. During the multiple thermal test cycles, test results of interferometric test, thermal IR images of the front face were recorded in order to validate thermal optical model

Cryogenic Optical Performance of a Light-weight Mirror Assembly for Future Space Astronomical Telescopes: Optical Test Results and Thermal Optical Model

A 40 cm diameter mirror assembly was interferometrically tested at room temperature down to 250 degrees Kelvin for thermal deformation. The 2.5 m radius of curvature spherical mirror assembly was constructed by low temperature fusing three abrasive waterjet core sections between two face sheets. The 93% lightweighted Corning ULE mirror assembly represents the current state of the art for future UV, optical, near IR space telescopes. During the multiple thermal test cycles, test results of interferometric test, thermal IR images of the front face were recorded in order to validate thermal optical model

Development of aerodynamic disturbance test procedures. Volume II: technical report. Final report.

National Highway Traffic Safety Administration, Vehicle Engineering Research Division, Washington, D.C.Mode of access: Internet.Author corporate affiliation: Systems Technology, Inc., Hawthorne, Calif.Report covers the period 30 Sept 1977-30 March 1979. Contract amount - $245,014Subject code: DBBSubject code: DEBSubject code: DECSubject code: DECSSubject code: DEDHSubject code: DEFFSubject code: DGBQSubject code: MAKCSubject code: NHDFSubject code: NMISubject code: NVEBSubject code: WVSSubject code: XQC

Development of aerodynamic disturbance test procedures. Volume I: executive summary. Final report.

National Highway Traffic Safety Administration, Vehicle Engineering Research Division, Washington, D.C.Mode of access: Internet.Author corporate affiliation: Systems Technology, Inc., Hawthorne, Calif.Report covers the period 30 Sept 1977-30 March 1979. Contract amount - $245,014Subject code: DBBSubject code: DEBSubject code: DECSubject code: DECSSubject code: DEDHSubject code: DEFFSubject code: DGBQSubject code: MAKCSubject code: NHDFSubject code: NMISubject code: NVEBSubject code: WVSSubject code: XQC

Systems Technology, Inc

Parachute flight simulation training originated as a low cost solution to improve the safety and performance of smokejumper canopy control. Improvements such as virtual reality head mounted displays, trackers and photorealistic graphics, and additional parachute control sensors have been added in response to military requirements for aircrew emergency and operational parachute training, including topics such as decision altitudes, chute deployment, malfunctions, equipment procedures, maneuvering, and landing

Systems Technology, Inc

Emergencies that lead to ejection and egress parachuting are dynamic, highly stressful and dangerous events. They require rapid application of skills taught long before. Virtual Reality (VR) parachute simulation training has become a widespread and accepted standard in U.S. and foreign, Navy and Air Force Aviation Physiology, Survival, and Life Support training 1 . As the process of supporting evaluation studies, making installations, and interacting with training personnel has progressed, a number of observations and suggestions have been made and incorporated, resulting in a more complete training capability. The trainee now can be fully equipped with, and required to utilize helmet, visor, oxygen mask, and other equipment, including manual, AAD (Automatic Activation Device), and Oxygen release handles for egress situations as shown in Figure 1. Thus the trainee now can actively participate in a dynamic VR experience that produces many of the same sensory and procedural demands as might be experienced in a real emergency . Results of correct or incorrect actions are automatically displayed and scored, and a number of other program features are provided to facilitate instructor to student critique

Development of tire intermix performance and inspection system. Volume II: technical report. Final report.

National Highway Traffic Safety Administration, Washington, D.C.Mode of access: Internet.Author corporate affiliation: Systems Technology, Inc., Hawthorne, Calif.Report covers the period April 1979-Jan 1981. Contract amount $212,464Subject code: DPCSubject code: DPCESubject code: NVBEBBSubject code: NVMSubject code: NVMBCSubject code: WVPSubject code: YC