The characteristics and capabilities are described of solar electric propulsion (SEP) for performing Mars Surface Sample Return (MSSR) missions. The scope of the study emphasizes trajectory/payload analysis and the comparison of mission/system tradeoff options. The MSSR mission is examined only for the 1981-82 launch opportunity. Several other study constraints which bear directly on the results obtained are: (1) return samples in the range 5-25 kg, (2) use of lifting (offset C.G.) atmospheric entry at Mars which allows a low ratio (1.25) of entry weight to landed weight, and (3) rendezvous and docking in Mars orbit. Major results of the study are presented as performance curves of earth departure mass versus sample size for a number of different mission/system options. These options represent a spectrum of trip time, launch vehicle capability, combinations of low-thrust and ballistic maneuvers, chemical retro type, and earth recovery mode.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Mars surface sample return missions via solar electric propulsion


    Contributors:

    Publication date :

    1971-08-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    MARS Surface Sample Return Missions Via Solar Electric Propulsion

    D. J. Spadoni / A. L. Friedlander | NTIS | 1971


    Round-Trip Solar Electric Propulsion Missions for Mars Sample Return

    Bailey, Zachary J. / Sturm, Erick J. / Kowalkowski, Theresa D. et al. | NTRS | 2014


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

    Donahue, Benjamin B. / Green, Shaun E. / Coverstone, Victoria L. et al. | NTRS | 2004


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

    B. B. Donahue / S. E. Green / V. L. Coverstone et al. | NTIS | 2004