Attitude control system is investigated assuming that satellite can be analyzed as thin circular plate; certain types of orbiting telescopes fall in this category; modes of vibration of system are determined and their influence on performance quality of three-axis control system is studied; it is shown that elastic motions are reflected on only one axis of vehicle with proper location of sensors, and that control system can be made insensitive to two lowest vibration modes; interaxis coupling has negligible influence on system stability if control system for each axis is properly designed.


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    Title :

    Attitude control problem for flexible satellites


    Additional title:

    SAE-NASA -- Proc


    Contributors:

    Conference:

    Proceedings of Society of Automotive Engineers, National Aeronautics and Space Administration -- Aerospace Vehicle Flight Control Conference ; 1965 Control



    Publication date :

    1965


    Size :

    11 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English


    Keywords :


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