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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    Title :

    Variable point guidance for space missions


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1966


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Variable point guidance for space missions

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



    Linear guidance laws for space missions

    TEMPELMAN, W. | AIAA | 1986