A managed disposal approach is proposed that would place the nuclear stage or vehicle in a highly stable orbit at modest cost to mission performance. The approach requires only a small increase in initial mass in LEO, but should be included in preliminary trajectory design and performance calculations. The mass penalty is expected to be larger for all-up flight profiles, or in cases of high-thrust propulsion systems for the cargo vehicle.


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    Title :

    Disposal modes for Mars transfer nuclear propulsion


    Contributors:

    Publication date :

    1991-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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