Nuclear-powered ion propulsion technology was combined with detailed trajectory analysis to determine propulsion system and trajectory options for an unmanned cargo mission to Mars in support of manned Mars missions. A total of 96 mission scenarios were identified by combining two power levels, two propellants, four values of specific impulse per propellant, three starting altitudes, and two starting velocities. Sixty of these scenarios were selected for a detailed trajectory analysis; a complete propulsion system study was then conducted for 20 of these trajectories. Trip times ranged from 344 days for a xenon propulsion system operating at 300 kW total power and starting from lunar orbit with escape velocity, to 770 days for an argon propulsion system operating at 300 kW total power and starting from nuclear start orbit with circular velocity. Trip times for the 3 MW cases studied ranged from 356 to 413 days. Payload masses ranged from 5700 to 12,300 kg for the 300 kW power level, and from 72,200 to 81,500 kg for the 3 MW power level.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Nuclear powered Mars cargo transport mission utilizing advanced ion propulsion


    Contributors:

    Publication date :

    1987-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Nuclear powered Mars cargo transport mission utilizing advanced ion propulsion

    Galecki, Diane L. / Patterson, Michael J. | NTRS | 1987


    Nuclear powered Mars cargo transport mission utilizing advanced ion propulsion

    Galecki, D.L. / Patterson, M.J. | Tema Archive | 1987




    Advanced propulsion options for the Mars cargo mission

    FRISBEE, ROBERT / BLANDINO, JOHN / SERCEL, JOEL et al. | AIAA | 1990