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  • 1
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    Digital adaptive controllers for VTOL vehicles. Volume 2: Software documentation (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The VTOL approach and landing test (VALT) adaptive software is documented. Two self-adaptive algorithms, one based on an implicit model reference design and the other on an explicit parameter estimation technique were evaluated. The organization of the software, user options, and a nominal set of input data are presented along with a flow chart and program listing of each algorithm.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-159154-VOL-2 , HONEYWELL-2825-41592-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Digital adaptive controllers for VTOL vehicles. Volume 1: Concept evaluation (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digital self-adaptive flight control system was developed for flight test in the VTOL approach and landing technology (VALT) research aircraft (a modified CH-47 helicopter). The control laws accept commands from an automatic on-board guidance system. The primary objective of the control laws is to provide good command-following with a minimum cross-axis response. Three attitudes and vertical velocity are separately commanded. Adaptation of the control laws is based on information from rate and attitude gyros and a vertical velocity measurement. The final design resulted from a comparison of two different adaptive concepts--one based on explicit parameter estimates from a real-time maximum-likelihood estimation algorithm, the other based on an implicit model reference adaptive system. The two designs were compared on the basis of performance and complexity.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-159154-VOL-1 , HONEYWELL-2825-41592-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Advanced flight control system study (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A fly by wire flight control system architecture designed for high reliability includes spare sensor and computer elements to permit safe dispatch with failed elements, thereby reducing unscheduled maintenance. A methodology capable of demonstrating that the architecture does achieve the predicted performance characteristics consists of a hierarchy of activities ranging from analytical calculations of system reliability and formal methods of software verification to iron bird testing followed by flight evaluation. Interfacing this architecture to the Lockheed S-3A aircraft for flight test is discussed. This testbed vehicle can be expanded to support flight experiments in advanced aerodynamics, electromechanical actuators, secondary power systems, flight management, new displays, and air traffic control concepts.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-163117 , NAS 1.26:163117 , HONEYWELL-82SRC5
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Adaptive control laws for F-8 flight test (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: This paper describes an adaptive flight control system design for NASA's F-8 digital fly-by-wire research aircraft. This design implements an explicit parallel maximum likelihood identification algorithm to estimate key aircraft parameters. The estimates are used to compute gains in simplified quadratic-optimal command augmentation control laws. Design details for the control laws and identifier are presented, and performance evaluation results from NASA Langley's F-8 Simulator are summarized.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: IEEE Transactions on Automatic Control; AC-22; Oct. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Adaptive control laws for F-8 flight tests (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An adaptive flight-control-system design for NASA's F-8 Digital Fly-by-Wire research aircraft is described. This design implements an explicit parallel maximum likelihood identification algorithm to estimate key aircraft parameters. The estimates are used to compute gains in simplified quadratic-optimal command augmentation control laws. Design details for the control laws and identifier are presented, and performance evaluation results from NASA Langley's F-8 simulator are summarized.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA. Ames Res. Center Systems Reliability Issues for Future Aircraft; p 27-49
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    F-8C adaptive control law refinement and software development (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An explicit adaptive control algorithm based on maximum likelihood estimation of parameters was designed. To avoid iterative calculations, the algorithm uses parallel channels of Kalman filters operating at fixed locations in parameter space. This algorithm was implemented in NASA/DFRC's Remotely Augmented Vehicle (RAV) facility. Real-time sensor outputs (rate gyro, accelerometer, surface position) are telemetered to a ground computer which sends new gain values to an on-board system. Ground test data and flight records were used to establish design values of noise statistics and to verify the ground-based adaptive software.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-163093 , HONEYWELL-77SRC53
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Digital adaptive control laws for the F-8 (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: NASA is conducting a flight control research program in digital fly-by-wire technology using a modified F-8C aircraft. The first phase of this program used Apollo hardware to demonstrate the practicality of digital fly-by-wire in an actual test vehicle. For the second phase, conventional aircraft sensors and a large floating point digital computer are being utilized to test advanced control laws and redundancy concepts. As part of NASA's research in digital fly-by-wire technology, Honeywell developed digital adaptive flight control laws for flight test in the F-8C. Adaptation of the control laws was to be based on information sensed from conventional aircraft sensors excluding air data. The control laws were constrained to use only existing elevator, rudder, and ailerons as control effectors, each powered by existing actuators. Three adaptive control laws were successfully designed using maximum likelihood estimation, a Liapunov stable model tracker and a self-excited limit cycle concept. The maximum likelihood estimation design was selected as the most promising because of its capability to identify more than surface effectiveness parameters. The adaptive concepts, the control laws and comparisons of predicted performance are described.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 76-1952 , Guidance and Control Conference; Aug 16, 1976 - Aug 18, 1976; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Digital adaptive control laws for VTOL aircraft (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Honeywell has designed a digital self-adaptive flight control system for flight test in the VALT Research Aircraft (a modified CH-47). The final design resulted from a comparison of two different adaptive concepts: one based on explicit parameter estimates from a real-time maximum likelihood estimation algorithm and the other based on an implicit model reference adaptive system. The two designs are compared on the basis of performance and complexity.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: 1978 Conference on Decision and Control; Jan 10, 1979 - Jan 12, 1979; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Flight test experience with an adaptive control system using a maximum likelihood parameter estimation technique (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The flight test performance of an adaptive control system for the F-8 DFBW aircraft is summarized. The adaptive system is based on explicit identification of surface effectiveness parameters which are used for gain scheduling in a command augmentation system. Performance of this control law under various design parameter variations is presented. These include variations in test signal level, sample rate, and identification channel structure. Flight performance closely matches analysis and simulation predictions from previous references.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 79-1702 , Guidance and Control Conference; Aug 06, 1979 - Aug 08, 1979; Boulder, CO
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Flight data processing with the F-8 adaptive algorithm (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An explicit adaptive control algorithm based on maximum likelihood estimation of parameters has been designed for NASA's DFBW F-8 aircraft. To avoid iterative calculations, the algorithm uses parallel channels of Kalman filters operating at fixed locations in parameter space. This algorithm has been implemented in NASA/DFRC's Remotely Augmented Vehicle (RAV) facility. Real-time sensor outputs (rate gyro, accelerometer and surface position) are telemetered to a ground computer which sends new gain values to an on-board system. Ground test data and flight records were used to establish design values of noise statistics and to verify the ground-based adaptive software. The software and its performance evaluation based on flight data are described
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 77-1042 , Guidance and Control Conference; Aug 08, 1977 - Aug 10, 1977; Hollywood, FL
    Format: text
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    NASA TECHNICAL REPORTS
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