A mathematical description of the data reduction technique used to simultaneously calibrate the Voyager celestial and inertial attitude control subsystems is given. It is shown that knowledge of the spacecraft limit cycle motion, as measured by the celestial and the inertial sensors, is adequate to result in the estimates of a selected number of errors which adversely affect the spacecraft attitude knowledge.


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    Title :

    Simultaneous Calibrations of Voyager Celestial and Inertial Attitude Control Systems in Flight


    Contributors:


    Publication date :

    1982-01-01


    Size :

    1802992 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English