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Round-trip solar electric propulsion missions for Mars sample return

Show simple item record Bailey, Zachary J. Sturm, Erick J. Kowalkowski, Theresa D. Lock, Robert E. Woolley, Ryan C. Nicholas, Austin K. 2016-06-06T19:02:11Z 2016-06-06T19:02:11Z 2014-01-26
dc.identifier.citation 24th AAS/AIAA Space Flight Mechanics Meeting, Santa Fe, New Mexico, January 26-30, 2014 en_US
dc.identifier.clearanceno 14-0432
dc.description.abstract Mars Sample Return (MSR) missions could benefit from the high specific impulse of Solar Electric Propulsion (SEP) to achieve lower launch masses than with chemical propulsion. SEP presents formulation challenges due to the coupled nature of launch vehicle performance, propulsion system, power system, and mission timeline. This paper describes a SEP orbiter-sizing tool, which models spacecraft mass & timeline in conjunction with low thrust round-trip Earth-Mars trajectories, and presents selected concept designs. A variety of system designs are possible for SEP MSR orbiters, with large dry mass allocations, similar round-trip durations to chemical orbiters, and reduced design variability between opportunities. en_US
dc.description.sponsorship NASA/JPL en_US
dc.language.iso en_US en_US
dc.publisher Pasadena, CA : Jet Propulsion Laboratory, National Aeronautics and Space Administration, 2014 en_US
dc.subject MSR en_US
dc.subject SEP en_US
dc.subject Mars Sample Return en_US
dc.subject Solar Electric Propulsion en_US
dc.subject Orbiter en_US
dc.title Round-trip solar electric propulsion missions for Mars sample return en_US
dc.type Preprint en_US

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