Mathematical analysis of problem for rocket with constant thrust acceleration going from one planetary orbit to another, employing formal methods of calculus of variations; results of numerical integration for thrust-to-mass ratio of 10-4 "g" 's and final to initial radius ratio of 1.5.


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    Title :

    Low-thrust rocket steering program for minimum time transfer between planetary orbits


    Additional title:

    Soc Automotive Engrs -- Paper


    Contributors:

    Conference:

    Society of Automotive Engineers -- Meeting ; 1958 Thrust



    Publication date :

    1958


    Size :

    20 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English