Conceptual in-space transfer stages, including those utilizing solar electric propulsion, chemical propulsion, and chemical propulsion with aerobraking or aerocapture assist at Mars, were evaluated. Roundtrip Mars sample return mission vehicles were analyzed to determine how specific system technology selections influence payload delivery capability. Results show how specific engine, thruster, propellant, capture mode, trip time and launch vehicle technology choices would contribute to increasing payload or decreasing the size of the required launch vehicles. Heliocentric low-thrust trajectory analyses for Solar Electric Transfer were generated with the SEPTOP code.


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    Title :

    Chemical and Solar Electric Propulsion Systems Analyses for Mars Sample Return Missions



    Conference:

    AIAA/ASME Joint Propulsion Conference ; 2004 ; Fort Lauderdale, FL, United States


    Publication date :

    2004-06-15


    Type of media :

    Preprint


    Type of material :

    No indication


    Language :

    English




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