The problem of finite-time control for attitude tracking maneuver of a rigid spacecraft is investigated. External disturbance, unknown inertia parameters are addressed. As stepping stone, a sliding mode controller is designed. It requires the upper bound of the lumped uncertainty including disturbance and inertia matrix. However, this upper bound may not be easily obtained. Therefore, an adaptive sliding mode control law is then proposed to release that drawback. Adaptive technique is applied to estimate that bound. It is proved that the closed-loop attitude tracking system is finite-time stable. The tracking errors of the attitude and the angular velocity are asymptotically stabilized. Moreover, the upper bound on the lumped uncertainty can be exactly estimated in finite time. The attitude tracking performance with application of the control scheme is evaluated through a numerical example. © 2014 Mingyi Huo et al.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Finite-time control for attitude tracking maneuver of rigid satellite



    Erscheinungsdatum :

    2014-01-01



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    Klassifikation :

    DDC:    629



    Fast satellite attitude maneuver and control

    Ye, Dong / Li, You / Xiao, Yan | TIBKAT | 2022




    Finite-Time Attitude Trajectory Tracking Control of Rigid Spacecraft

    Xiao-Ning Shi, / Zhi-Gang Zhou, / Di Zhou, | IEEE | 2017


    Robust Finite-Time Control for Flexible Spacecraft Attitude Maneuver

    Wu, Shunan / Radice, Gianmarco / Sun, Zhaowei | ASCE | 2012