A nonlinear control scheme for attitude control of a spacecraft is combined with a nonlinear gyro bias observer for the case of constant gyro bias. The closed loop system is proven to be globally stable, with zero tracking error, thus proving a separation principle for the given system. The nonlinear observer incorporates persistency of excitation, resulting in exponential convergence of the gyro bias error.


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    Titel :

    A Coupled Nonlinear Spacecraft Attitude Controller/Observer With an Unknown Constant Gyro Bias


    Beteiligte:

    Kongress:

    40th IEEE Conference on Decision and Control ; 2001 ; United States


    Erscheinungsdatum :

    01.01.2001


    Medientyp :

    Preprint


    Format :

    Keine Angabe


    Sprache :

    Englisch