Analytic solutions are determined for optimum correction of all 6 elements of elliptic satellite orbits with low-thrust, power-limited propulsion systems; optimum direction and magnitude of thrust are determined as functions of time so as to minimize fuel required to rendezvous in given time or to minimize fuel required for station keeping in presence of known perturbations; solutions obtained are divided into 2 classes, depending on whether rendezvous requires few or many revolutions; in latter case, simple analytic solutions are obtained by neglecting short-period perturbations.


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    Titel :

    Optimum low-thrust rendezvous and station keeping


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Edelbaum, T.N. (Autor:in)

    Erschienen in:

    AIAA Journal ; 2 , n 7


    Erscheinungsdatum :

    1964


    Format / Umfang :

    6 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :




    Optimum Low-Thrust Rendezvous and Station Keeping

    Theodore N. Edelbaum | AIAA | 2003