A multi-input, multi-output reconfigurable flight control system design utilizing a robust controller and an adaptive filter is presented. The robust control design consists of a reduced-order, linear dynamic inversion controller with an outer-loop compensation matrix derived from Quantitative Feedback Theory (QFT). A principle feature of the scheme is placement of the adaptive filter in series with the QFT compensator thus exploiting the inherent robustness of the nominal flight control system in the presence of plant uncertainties. An example of the scheme is presented in a pilot-in-the-loop computer simulation using a simplified model of the lateral-directional dynamics of the NASA F18 High Angle of Attack Research Vehicle (HARV) that included nonlinear anti-wind up logic and actuator limitations. Prediction of handling qualities and pilot-induced oscillation tendencies in the presence of these nonlinearities is included in the example.


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    Title :

    Reconfiguration Scheme for Accommodating Actuator Failures in Multi-Input, Multi-Output Flight Control Systems


    Contributors:
    W. Siwakosit (author) / R. A. Hess (author)

    Publication date :

    2000


    Size :

    20 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






    Accommodating Actuator Failures in Flight Control Systems

    Hess, R. A. / Siwakosit, W. / Chung, J. et al. | British Library Conference Proceedings | 1999


    Accommodating Actuator Failures in Flight Control Systems

    Hess, R. A. / Siwakosit, W. / Chung, J. | NTRS | 1998


    Accommodating actuator failures in flight control systems

    Hess, R. / Siwakosit, W. / Chung, J. | AIAA | 1999