Explicit space guidance scheme, which combines phasing and propellant advantages of parking orbits with rapid response time of direct ascent, is described; resulting flight plans yield multiburn trajectories spanning continuum from direct ascent (2-burns) to parking orbit approaches (4 or more burns); onboard computer selects automatically and continuously flight plan depending on instantaneous geometry; system reaction time to arbitrary mission situation is measured in seconds; results of computer sizing study are presented, showing that scheme can be implemented in aerospace computer; scheme, developed for satellite rendezvous, is applicable to emergency rescue missions or any mission requiring injection of payloads into precise Earth orbits.


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    Titel :

    Variable point guidance for space missions


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Schneider, A.M. (Autor:in) / Capen, E.B. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1966


    Format / Umfang :

    8 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Variable point guidance for space missions

    CAPEN, E. / SCHNEIDER, A. | AIAA | 1964



    Linear guidance laws for space missions

    TEMPELMAN, W. | AIAA | 1986