Methods of deriving the dynamic equations of motion of three-axis stabilized satellites with large flexible solar arrays and/or antennas, described in literature, are compared and summarized. Approaches adopted for analyzing flexible structures are discussed and their impact on the formulation of the dynamic equations is considered. A discussion of papers describing the design and synthesis of a suitable control law for a three-axis stabilized satellite with flexible appendages is presented.


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    Title :

    The Attitude Control of Three-Axis Stabilised Spacecraft with Flexible Appendages, Volume 1


    Contributors:
    R. S. Harris (author) / D. C. Todman (author) / N. Swift (author)

    Publication date :

    1976


    Size :

    183 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English