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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    Title :

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


    Contributors:

    Conference:

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


    Publication date :

    2001-01-01


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English