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.


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    Title :

    Flight test experience with an adaptive control system using a maximum likelihood parameter estimation technique


    Contributors:
    Hartmann, G. (author) / Stein, G. (author) / Powers, B. (author)

    Conference:

    Guidance and Control Conference ; 1979 ; Boulder, CO


    Publication date :

    1979-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English






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