Analysis on the attitude controller based upon moment of inertia distribution for a bias momentum satellite is discussed. Spacecraft moment of inertia distribution is represented in the form of product of inertia terms in the system inertia matrix. The product of inertia between orthogonal body axes of the satellite is used to build a controller which controls the nutational motion caused by the angular momentum of the wheel. The attitude controller in the pitch axis controlling the pitch motion as well as nutational dynamics in the roll/yaw planes is analyzed in detail. Analytic expressions using linearized equations are derived providing further insight into the dynamic coupling effect among orthogonal body axes.


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    Title :

    Attitude control of a bias momentum satellite using moment of inertia


    Contributors:


    Publication date :

    2002-01-01


    Size :

    267753 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English