The attitude motion of a tumbling, rigid, axisymmetric spacecraft is considered. A methodology for detumbling the spacecraft through energy dissipation is presented. The differential equations governing this motion are stiff, and therefore an approximate solution, based on the variation of constants method, is developed and utilized in the analysis of the detumbling strategy. Stability of the detumbling process is also addressed.


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    Title :

    Spacecraft Detumbling through Energy Dissipation


    Contributors:
    N. Fitz-coy (author) / A. Chatterjee (author)

    Publication date :

    1993


    Size :

    15 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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