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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

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


    Beteiligte:
    R. S. Harris (Autor:in) / D. C. Todman (Autor:in) / N. Swift (Autor:in)

    Erscheinungsdatum :

    1976


    Format / Umfang :

    183 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch