A satellite attitude control system is usable in the absence of any inertial yaw attitude reference, such as a gyroscope, and in the absence of a pitch bias momentum. Both the roll-yaw rigid body dynamics and the roll-yaw orbit kinematics are modelled. Pitch and roll attitude control are conventional. The model receives inputs from a roll sensor, and roll and yaw torques from reaction wheel monitors. The model produces estimated yaw which controls the spacecraft yaw attitude.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Gyroless yaw control system for a three axis stabilized, zero-momentum spacecraft


    Contributors:

    Publication date :

    1993-04-27


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    A Gyroless Yaw Attitude Estimator For NOAA-11 - A Zero Momentum Spacecraft (AAS 93-296)

    Stetson, J. B. / American Astronautical Society / United States; National Aeronautics and Space Administration et al. | British Library Conference Proceedings | 1993


    Position-based gyroless control of spacecraft attitude

    LIU DAN Y / CHIANG RICHARD Y | European Patent Office | 2015

    Free access

    Spacecraft Acquisiton Maneuvers Using Position-Based Gyroless Control

    LIU DAN Y / CHIANG RICHARD Y | European Patent Office | 2017

    Free access

    Gyroless fine pointing on Small Explorer Spacecraft

    Bauer, Frank H. / Dellinger, Wayne | NTRS | 1993


    Gyroless Fine Pointing on Small Explorer Spacecraft

    Bauer, F. / Dellinger, W. / AIAA | British Library Conference Proceedings | 1993