A method is presented for open loop guidance of a solar electric propulsion spacecraft to geosynchronsus orbit. The method consists of determining the thrust vector profiles on the ground with an optimization computer program, and performing updates based on the difference between the actual trajectory and that predicted with a precision simulation computer program. The motivation for performing the guidance analysis during the mission planning phase is discussed, and a spacecraft design option that employs attitude orientation constraints is presented. The improvements required in both the optimization program and simulation program are set forth, together with the efforts to integrate the programs into the ground support software for the guidance system. (Author)


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    Title :

    Development of a Unified Guidance System for Geocentric Transfer


    Contributors:
    J. E. Cake (author) / J. D. Regetz (author)

    Publication date :

    1975


    Size :

    13 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Development of a unified guidance system for geocentric transfer

    Cake, J. E. / Regetz, J. D., Jr. | NTRS | 1975



    Development of a unified guidance system for geocentric transfer

    Cake, J. E. / Regetz, J. D., Jr. | NTRS | 1975


    Solar-electric geocentric transfer

    Malchow, H. L. / Sackett, L. L. | NTRS | 1979


    Optimal low thrust geocentric transfer

    EDELBAUM, T. / SACKETT, L. / MALCHOW, H. | AIAA | 1973