AbstractThis paper studies the active optimal attitude control of a three-axis stabilized flexible spacecraft by flywheels. Without neglecting the second order terms in the model of attitude dynamics, the flexible spacecraft with vibration solar arrays is a nonlinear system. The nonlinear system is recursively approximated as a sequence of linear and time-varying systems, and the corresponding time-varying linear quadratic regulators (LQR) are designed for the approximated systems, so that a given optimization criterion is minimized. The results of numerical simulation show that the time-varying LQR designed gives satisfactory results in attitude maneuver and vibration suppression control for the nonlinear flexible spacecraft.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Optimal attitude control for three-axis stabilized flexible spacecraft


    Beteiligte:
    Zheng, Jianhua (Autor:in) / Banks, Stephen P. (Autor:in) / Alleyne, Hugo (Autor:in)

    Erschienen in:

    Acta Astronautica ; 56 , 5 ; 519-528


    Erscheinungsdatum :

    2004-10-11


    Format / Umfang :

    10 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





    Flexible Spacecraft Three Axis Attitude Maneuver by Active Vibration Control

    M. Sayanjali / J. Roshanian / A. Ghafari | DOAJ | 2009

    Freier Zugriff

    A flexible attitude control system for three-axis stabilized nanosatellites

    Gordon, Karsten / Technische Universität Berlin / Technische Universität Berlin, Universitätsbibliothek | TIBKAT | 2018


    Three Axis Authority Momentum Spacecraft Attitude Control

    Barker, L. / Price, X. / Rodden, J. | AIAA | 2002