Two strategies are presented for semi-autonomous on-board trajectory propagation. One implements a semi-analytic method and rectifies, when needed, a simple on-board (on-line) ephemeris. The method is called rectification in which only several parameters are uplinked to the spacecraft infrequently. The other strategy uses TOPEX/POSEIDON experience to build a data compression device for a wide range of orbits. A trade-off study is conducted to relate accuracy requirements with semi-major axis and eccentricity to minimize the frequency of uplinking.


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    Title :

    Semi-Autonomous Spacecraft On-Board Ephemeris Propagation


    Contributors:
    Kangas, J. (author) / Salama, A. (author)

    Publication date :

    1995-08-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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