Emphasis of the electric propulsion technology program is now on the application of solar electric propulsion to scientific missions. Candidate planetary, cometary, and geosynchronous missions are being studied. The object of this paper is to describe a basic spacecraft design proposed as the means to accomplish (1) a comet Encke slow flyby, (2) a comet Encke rendezvous, and (3) an out-of-the-ecliptic mission. The discussion includes design differences foreseen for the various missions and indicates those areas where spacecraft design commonality is possible. Particular emphasis is placed on a solar electric propulsion module design which permits an attractive degree of design inheritance from mission to mission.


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    Title :

    Interplanetary spacecraft design using solar electric propulsion


    Contributors:

    Conference:

    American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference ; 1974 ; San Diego, CA


    Publication date :

    1974-10-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





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