A methodology is presented for the design of flight control systems that exhibit stability and performance-robustness in the presence of actuator failures. The design is based upon two elements. The first element consists of a control law that will ensure at least stability in the presence of a class of actuator failures. This law is created by inner-loop, reduced-order, linear dynamic inversion, and outer-loop compensation based upon Quantitative Feedback Theory. The second element consists of adaptive compensators obtained from simple and approximate time-domain identification of the dynamics of the 'effective vehicle' with failed actuator(s). An example involving the lateral-directional control of a fighter aircraft is employed both to introduce the proposed methodology and to demonstrate its effectiveness and limitations.


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    Title :

    Development of a Design Methodology for Reconfigurable Flight Control Systems


    Contributors:

    Conference:

    Aerospace Sciences ; 2000 ; Reno, NV, United States


    Publication date :

    2000-01-01


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English




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