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  • 1
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    Flight research simulation takes off (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The simulation configurations used in research flight test, including nonreal-time, real-time all-software, hardware-in-the-loop, iron bird, and aircraft-in-the-loop, are reviewed. It is concluded that progress in simulation technology will demonstrate new concepts, evaluate designs, enhance the quality of flight test, and minimize flight risks.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace America (ISSN 0740-722X); 31; 8; p. 18-21.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Verification and Validation of Neural Networks for Aerospace Systems (2002)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Dryden Flight Research Center V&V working group and NASA Ames Research Center Automated Software Engineering (ASE) group collaborated to prepare this report. The purpose is to describe V&V processes and methods for certification of neural networks for aerospace applications, particularly adaptive flight control systems like Intelligent Flight Control Systems (IFCS) that use neural networks. This report is divided into the following two sections: 1) Overview of Adaptive Systems; and 2) V&V Processes/Methods.
    Keywords: Cybernetics, Artificial Intelligence and Robotics
    Format: application/pdf
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  • 3
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    A knowledge-based system design/information tool for aircraft flight control systems (1991)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Research aircraft have become increasingly dependent on advanced electronic control systems to accomplish program goals. These aircraft are integrating multiple disciplines to improve performance and satisfy research objective. This integration is being accomplished through electronic control systems. Systems design methods and information management have become essential to program success. The primary objective of the system design/information tool for aircraft flight control is to help transfer flight control system design knowledge to the flight test community. By providing all of the design information and covering multiple disciplines in a structured, graphical manner, flight control systems can more easily be understood by the test engineers. This will provide the engineers with the information needed to thoroughly ground test the system and thereby reduce the likelihood of serious design errors surfacing in flight. The secondary object is to apply structured design techniques to all of the design domains. By using the techniques in the top level system design down through the detailed hardware and software designs, it is hoped that fewer design anomalies will result. The flight test experiences are reviewed of three highly complex, integrated aircraft programs: the X-29 forward swept wing; the advanced fighter technology integration (AFTI) F-16; and the highly maneuverable aircraft technology (HiMAT) program. Significant operating technologies, and the design errors which cause them, is examined to help identify what functions a system design/informatin tool should provide to assist designers in avoiding errors.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AGARD, Knowledge Based System Applications for Guidance and Control; 14 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Development and flight test experiences with a flight-crucial digital control system (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Engineers and scientists in the advanced fighter technology integration (AFTI) F-16 program investigated the integration of emerging technologies into an advanced fighter aircraft. AFTI's three major technologies included: flight-crucial digital control, decoupled aircraft flight control, and integration of avionics, flight control, and pilot displays. In addition to investigating improvements in fighter performance, researchers studied the generic problems confronting the designers of highly integrated flight-crucial digital control. An overview is provided of both the advantages and problems of integration digital control systems. Also, an examination of the specification, design, qualification, and flight test life-cycle phase is provided. An overview is given of the fault-tolerant design, multimoded decoupled flight control laws, and integrated avionics design. The approach to qualifying the software and system designs is discussed, and the effects of design choices on system qualification are highlighted.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2857 , H-1344 , NAS 1.60:2857
    Format: application/pdf
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  • 5
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    Verification and Validation Methodology of Real-Time Adaptive Neural Networks for Aerospace Applications (2004)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Recent research has shown that adaptive neural based control systems are very effective in restoring stability and control of an aircraft in the presence of damage or failures. The application of an adaptive neural network with a flight critical control system requires a thorough and proven process to ensure safe and proper flight operation. Unique testing tools have been developed as part of a process to perform verification and validation (V&V) of real time adaptive neural networks used in recent adaptive flight control system, to evaluate the performance of the on line trained neural networks. The tools will help in certification from FAA and will help in the successful deployment of neural network based adaptive controllers in safety-critical applications. The process to perform verification and validation is evaluated against a typical neural adaptive controller and the results are discussed.
    Keywords: Aircraft Stability and Control
    Type: International Conference on Computational Intelligence on Modeling, Control and Automation (CIMCA); Jul 12, 2004 - Jul 14, 2004; Gold Coast; Australia
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Overview of the NASA AMES-Dryden Integrated Test Facility (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Integrated Test Facility (ITF), being built at the NASA Ames Research Center's Dryden Flight Research Facility (ADFRF), will provide new real-time test capabilities for emerging research aircraft. An overview of the ITF and the real-time systems being developed to operate this unique facility are outlined in this paper. The ITF will reduce flight test risk by minimizing the difference between the flight- and ground-test environments. The ground-test environment is provided by combining real-time flight simulation with the actual aircraft. The generic capabilities of the ITF real-time systems, the real-time data recording, and the remotely augmented vehicle (RAV) monitoring system will be discussed. The benefits of applying simulation to aircraft-in-the-loop testing and RAV monitoring system capabilities to the X-29A flight research program will also be discussed.
    Keywords: Research and Support Facilities (Air)
    Type: NASA/TM-1999-101720 , NAS 1.15:101720 , H-1596 , 36th ASD/TMD Proceedings; May 07, 1990 - May 10, 1990; Denver, CO; United States
    Format: application/pdf
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  • 7
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    Verification and Validation of Neural Networks for Aerospace Systems (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The Dryden Flight Research Center V&V working group and NASA Ames Research Center Automated Software Engineering (ASE) group collaborated to prepare this report. The purpose is to describe V&V processes and methods for certification of neural networks for aerospace applications, particularly adaptive flight control systems like Intelligent Flight Control Systems (IFCS) that use neural networks. This report is divided into the following two sections: Overview of Adaptive Systems and V&V Processes/Methods.
    Keywords: Computer Programming and Software
    Type: NASA/CR-2002-211409 , NAS 1.26:211409
    Format: application/pdf
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  • 8
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    The X-33 Extended Flight Test Range (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Development of an extended test range, with range instrumentation providing continuous vehicle communications, is required to flight-test the X-33, a scaled version of a reusable launch vehicle. The extended test range provides vehicle communications coverage from California to landing at Montana or Utah. This paper provides an overview of the approaches used to meet X-33 program requirements, including using multiple ground stations, and methods to reduce problems caused by reentry plasma radio frequency blackout. The advances used to develop the extended test range show other hypersonic and access-to-space programs can benefit from the development of the extended test range.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking
    Type: NASA/TM-1998-206557 , NAS 1.15:206557 , H-2261 , International Telemetry Conference; Oct 26, 1980 - Oct 29, 1980; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    System overview of the NASA Dryden Integrated Test Facility (1992)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Integrated Test Facility, built at the NASA Dryden Flight Research Facility, provides new real-time test capabilities for emerging research aircraft. An overview of the test facility and the real-time systems developed to operate this unique facility is presented. The facility will reduce flight test risk by minimizing the difference between the flight and ground test environments. This ground test environment is provided by combining real-time flight simulation with the actual aircraft. A brief introduction to the facility is followed by a discussion of the generic capabilities of its real-time systems. The simulation system with flight hardware and the remotely augmented vehicle system is described. An overview of many hardware systems developed for the facility follows. The benefits of applying simulation to hardware-in-the-loop testing on the X-31 Flight Research Program are presented.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-104250 , H-1831 , NAS 1.15:104250 , Society of Flight Test Engineers 23rd Annual Symposium; Aug 01, 1992; Hauppage, NY; United States
    Format: application/pdf
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  • 10
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    Rapid development of the X-31 simulation to support flight-testing (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The X-31 Enhanced Fighter Maneuverability Program has been recognized to form the International Test Organization, with the NASA Dryden Flight Research Facility (NASA-Dryden) as the responsible test organization. The two X-31 research aircraft and engineering support personnel were colocated at NASA-Dryden, with flight test operations beginning in Apr. 1992. Therefore, rapid development of a hardware-in-the-loop simulation was needed to support the flight test operations at NASA-Dryden, and to perform verification and validation of flight control software. The X-31 simulation system requirements, distributed simulation system architecture, simulation components math models to the visual system, and the advanced capabilities the X-31 simulation provides. In addition, unique software tools and the methods used to rapidly develop this simulation system will be highlighted.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 92-4176 , ; 18 p.|AIAA and AHS, Flight Simulation Technologies Conference; Aug 24, 1992 - Aug 26, 1992; Hilton Head Island, SC; United States
    Format: text
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