Maneuvers in which orbital plane of earth satellite is changed by means of aerodynamic forces during one or more skips into and out of atmosphere are analyzed; characteristic velocities required of rockets to deflect vehicle into atmosphere and to reaccelerate it to orbital speed after leaving atmosphere are calculated as functions of change in inclination lift-drag ratio, and entry angle, and compared with characteristic velocities required for purely extra-atmospheric rocket maneuvers.


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    Title :

    Change of satellite orbit plane by aerodynamic maneuvering


    Additional title:

    J Aerospace Sciences


    Contributors:

    Published in:

    Publication date :

    1962


    Size :

    10 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :