A method of optimizing the apogee burns to maximize the worst-case beginning of life mass for a geosynchronous satellite is presented. Optimizing the worst-case rather than the nominal transfer strategy results in a reduction in the propellant mass required for the maneuver. A computer program written to implement the algorithm is described and the results of two case studies are presented. One of these case studies employs a single apogee engine burn with the thrust vector following a slew about a single spacecraft axis. The second employs a multiburn apogee engine maneuver with an inertially fixed thrust vector. Both cases show significant reductions in the propellant required for the 99th percentile case.


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    Titel :

    Optimization of Worst Case Perigee Raising Strategy


    Beteiligte:
    M. J. Smalley (Autor:in) / D. A. Young (Autor:in)

    Erscheinungsdatum :

    1986


    Format / Umfang :

    7 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch