Optimum thrust programs are used to generate rendezvous trajectories from Earth to Mars for various flight times and launch dates during years 1968 to 1971; manner in which propulsion requirements vary with flight time and launch date is considered; comparison of vehicle performance using variable and constant thrust programs; existence of optimum launch dates is interpreted in terms of certain transversality conditions derivable from calculus of variations; comparison of advanced propulsion and ballistic vehicle propulsion requirements for Earth-Mars rendezvous trajectories.


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    Title :

    Optimum interplanetary rendezvous with power-limited vehicles


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 1 , n 1


    Publication date :

    1963


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    OPTIMUM INTERPLANETARY RENDEZVOUS WITH POWER-LIMITED VEHICLES

    MELBOURNE, W. G. / SAUER, C. G. | AIAA | 1963


    OPTIMUM INTERPLANETARY RENDEZVOUS WITH POWER-LIMITED VEHICLES

    Melbourne, W. G. / Sauer, C. G., Jr. | NTRS | 1963




    SIMONE: Interplanetary microsatellites for NEO rendezvous missions

    Wells, N. / Walker, R. / Green, S. et al. | British Library Conference Proceedings | 2006