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  • 1
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    Interactive flight control system analysis program (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A summary of the development, use, and documentation of the interactive software (DIGIKON IV) for flight control system analyses is presented. A list of recommendations for future development is also included.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-172352 , NAS 1.26:172352 , REPT-84SRC10
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Active flutter control for flexible vehicles, volume 1 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An active flutter control methodology based on linear quadratic gaussian theory and its application to the control of a super critical wing is presented. Results of control surface and sensor position optimization are discussed. Both frequency response matching and residualization used to obtain practical flutter controllers are examined. The development of algorithms and computer programs for flutter modeling and active control design procedures is reported.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-159160-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Robust Kalman filter design for active flutter suppression systems (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Additional insight is provided into the use of the Doyle-Stein (1979, 1981) technique in aeroelastic control problems by examining the application of the method to a flutter control problem. The system to be controlled consists of a full-size wind tunnel model of a wing, plus an aileron, an actuator, and an accelerometer used to sense the motion of the wing. A full-state feedback controller was designed using linear optimal control theory, and a Kalman filter was used in the feedback loop for state estimation. The filter design procedure is explained along with that to improve closed-loop properties of the system. The locus of the poles of the filter is examined as a scalar design parameter is varied. The Doyle-Stein design procedure is shown to substantially improve the stability properties of an active flutter controller designed using the linear quadratic Gaussian control theory.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Active flutter suppression using Linear Quadratic Gaussian theory (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the application of Linear Quadratic Gaussian (LQG) methodology to the design of active control systems for suppression of aerodynamic flutter. A full-size wind tunnel model of a supercritical wing with associated sensors and actuators comprises the system to be controlled. Results of a synthesis methodology that provide small values of rms response, insensitivity to flight condition, and robust stability are presented. Results of control surface and sensor position optimization are also presented. Both frequency response matching and residualization are used to obtain practical flutter controllers.
    Keywords: STRUCTURAL MECHANICS
    Type: AIAA PAPER 80-1758 , Guidance and Control Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
    Format: text
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    NASA TECHNICAL REPORTS
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