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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    Title :

    Optimization of Worst Case Perigee Raising Strategy


    Contributors:
    M. J. Smalley (author) / D. A. Young (author)

    Publication date :

    1986


    Size :

    7 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English