Onboard computer equations for rocket vehicle guidance to elliptical orbit are developed; computational requirements are held to minimum, consistent with accurate orbital injection, near optimum fuel consumption, and explicit formulation; digital simulation results are shown for circular orbit injection with Saturn V vehicle; guidance scheme errors are less than 1 1/10 m/sec for disturbances caused by wind and variations in rocket engine parameters; payload loss caused by simplified guidance law is less than 1/10% of gross weight delivered to orbit. (17709)


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    Title :

    Simplified explicit guidance scheme for orbital injection


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1968


    Size :

    3 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English