An adaptive flight-control-system design for NASA's F-8 Digital Fly-by-Wire research aircraft is described. This design implements an explicit parallel maximum likelihood identification algorithm to estimate key aircraft parameters. The estimates are used to compute gains in simplified quadratic-optimal command augmentation control laws. Design details for the control laws and identifier are presented, and performance evaluation results from NASA Langley's F-8 simulator are summarized.


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    Title :

    Adaptive control laws for F-8 flight tests


    Contributors:


    Publication date :

    1975-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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