System considered consists of two space vehicles namely, target vehicle (nonmaneuvering vehicle) and interceptor vehicle (maneuvering vehicle) under influence of earth gravity; interceptor vehicle has propulsive jet systems which can produce variable thrust (positive or negative) independently in three perpendicular directions; case where target vehicle is in elliptic orbit is mainly considered and some analytical difficulties involved in circular orbit case are discussed; several time-optimal trajectories for different configurations are shown. (10923)


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    Title :

    Time-optimal rendezvous for elliptic orbits


    Additional title:

    NASA CR


    Contributors:

    Published in:

    Publication date :

    1968


    Size :

    114 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


    Time-optimal rendezvous for elliptic orbits

    Kashiwagi, Y. / Alfriend, K. T. | TIBKAT | 1968


    Time-optimal rendezvous for elliptic orbits

    Alfriend, K. T. / Kashiwagi, Y. | NTRS | 1968


    Minimum-time orbital rendezvous between neighboring elliptic orbits

    Alfriend, K. T. / Kashiwagi, Y. | NTRS | 1969