Abstract The problem of optimization of the interplanetary trajectory of flight for a multistage spacecraft with high- and low-thrust engines into the Jupiter satellite orbit is considered. Low-thrust engines (stationary plasma engines) are used on a heliocentric flight segment. Their operation is maintained with electric power supply from solar batteries. The principal feasibility of the realization of such a project is shown, and estimations of the mass of a spacecraft placed into Jupiter's satellite orbit are presented.


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    Title :

    The Use of a Solar Electrojet Propulsion System for Jupiter Satellite Injection


    Contributors:

    Published in:

    Cosmic Research ; 40 , 2 ; 186-193


    Publication date :

    2002-03-01


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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