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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Contributors:

    Publication date :

    2001


    Size :

    12 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English