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  • AIRCRAFT STABILITY AND CONTROL  (8)
  • 2000-2004
  • 1985-1989  (8)
  • 1960-1964
  • 1945-1949
  • 1
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    Evaluation of detectability and distinguishability of aircraft control element failures using flight test data (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper examines the detectability and distinguishability of control element failures on the B-737 aircraft. The results of Weiss (1985) are used to define decentralized residuals from analytic redundancy relationships, and the results of Weiss et al. (1984) are used to define the probabilistic distance measures which provide bounds on the minimum achievable probabilities or error. The residual signals are then generated using data which were recorded during a landing approach of the NASA-Langley Advanced Transport Operations (ATOPS) transportation systems research vehicle (TSRV). The distance measures are computed using estimates of the statistics of these residual signals.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Integrated restructurable flight control system demonstration results (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this study was to examine the complementary capabilities of several restructurable flight control system (RFCS) concepts through the integration of these technologies into a complete system. Performance issues were addressed through a re-examination of RFCS functional requirements, and through a qualitative analysis of the design issues that, if properly addressed during integration, will lead to the highest possible degree of fault-tolerant performance. Software developed under previous phases of this contract and under NAS1-18004 was modified and integrated into a complete RFCS subroutine for NASA's B-737 simulation. The integration of these modules involved the development of methods for dealing with the mismatch between the outputs of the failure detection module and the input requirements of the automatic control system redesign module. The performance of this demonstration system was examined through extensive simulation trials.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-178305 , NAS 1.26:178305 , TR-335
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    An automatic redesign approach for restructurable control systems (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents an approach to the automatic redesign of flight control systems for aircraft that have suffered one or more control element failures. The procedure is based on Linear Quadratic design techniques, and produces a control system that maximizes a measure of feedback system performance subject to a bandwidth constraint.
    Keywords: AIRCRAFT STABILITY AND CONTROL
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    NASA TECHNICAL REPORTS
  • 4
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    Investigation of an automatic trim algorithm for restructurable aircraft control (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper develops and solves an automatic trim problem for restructurable aircraft control. The trim solution is applied as a feed-forward control to reject measurable disturbances following control element failures. Disturbance rejection and command following performances are recovered through the automatic feedback control redesign procedure described by Looze et al. (1985). For this project the existence of a failure detection mechanism is assumed, and methods to cope with potential detection and identification inaccuracies are addressed.
    Keywords: AIRCRAFT STABILITY AND CONTROL
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    NASA TECHNICAL REPORTS
  • 5
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    Simulation results of automatic restructurable flight control system concepts (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The restructurable flight control system (RFCS) described by Weiss et al. (1986) is reviewed, and several results of an extensive six degrees of freedom nonlinear simulation of several aspects of this system are reported. It is concluded that the nontraditional use of standard control surfaces in a nominal feedback control system to spread control authority among many redundant control elements provides a significant amount of fault tolerance without any use of restructuring techniques. The use of new feedback gains alone following a failure can provide significantly improved recovery as long as the control elements remain within their travel limits and as long as uncertainty about the failure identity is properly handled. The use of the feed-forward trim solution in conjunction with redesigned feedback gains allows recovery to take place even when significant control saturation occurs.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 86-2032
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Initial design and evaluation of automatic restructurable flight control system concepts (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results of efforts to develop automatic control design procedures for restructurable aircraft control systems is presented. The restructurable aircraft control problem involves designing a fault tolerance control system which can accommodate a wide variety of unanticipated aircraft failure. Under NASA sponsorship, many of the technologies which make such a system possible were developed and tested. Future work will focus on developing a methodology for integrating these technologies and demonstration of a complete system.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-178064 , NAS 1.26:178064 , AI-TR-269
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Automatic control design procedures for restructurable aircraft control (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A simple, reliable automatic redesign procedure for restructurable control is discussed. This procedure is based on Linear Quadratic (LQ) design methodologies. It employs a robust control system design for the unfailed aircraft to minimize the effects of failed surfaces and to extend the time available for restructuring the Flight Control System. The procedure uses the LQ design parameters for the unfailed system as a basis for choosing the design parameters of the failed system. This philosophy alloys the engineering trade-offs that were present in the nominal design to the inherited by the restructurable design. In particular, it alloys bandwidth limitations and performance trade-offs to be incorporated in the redesigned system. The procedure also has several other desirable features. It effectively redistributes authority among the available control effectors to maximize the system performance subject to actuator limitations and constraints. It provides a graceful performance degradation as the amount of control authority lessens. When given the parameters of the unfailed aircraft, the automatic redesign procedure reproduces the nominal control system design.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-172489 , NAS 1.26:172489 , TR-212-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Integrated flight/propulsion control study for STOVL applications (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The STOVL Integrated Flight Propulsion Controls (IFPC) Program, initiated by NASA Lewis and NASA Ames to develop the necessary technologies for integrating the flight and propulsion controls of a future STOVL aircraft, is described. A major element of the STOVL IFPC Program is the STOVL Controls Integration Program (SCIP), which focuses on the development of an integrated flight propulsion control for the advanced vectored thrust STOVL concept. The SCIP has progressed to the point of generating top level control requirements.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 89-2908
    Format: text
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