This paper describes an adaptive flight control system design for NASA's F-8 digital fly-by-wire research aircraft. 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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Adaptive control laws for F-8 flight test


    Beteiligte:
    Stein, G. (Autor:in) / Hartmann, G. L. (Autor:in) / Hendrick, R. C. (Autor:in)


    Erscheinungsdatum :

    01.10.1977


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Developing a Flight Test Strategy for Adaptive Flight Control Laws

    Berra, Lee / Campbell, Christopher / Wilson, Taylor | AIAA | 2017


    Adaptive control laws for F-8 flight test

    Stein, G. / Hartmann, G.L. / Hendrick, R.C. | Tema Archiv | 1977


    DEVELOPING A FLIGHT TEST STRATEGY FOR ADAPTIVE FLIGHT CONTROL LAWS (AIAA 2017-3649)

    Berra, Lee / Campbell, Christopher / Wilson, Taylor | British Library Conference Proceedings | 2017


    F-8C Adaptive Flight Control Laws

    G. L. Hartmann / C. A. Harvey / G. Stein et al. | NTIS | 1977


    F-8C adaptive flight control laws

    Hartmann, G. L. / Harvey, C. A. / Stein, G. et al. | NTRS | 1977