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Electric propulsion system selection process for interplanetary missions

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dc.contributor.author Landau, Damon
dc.contributor.author Chase, James
dc.contributor.author Kowalkowski, Theresa
dc.contributor.author Oh, David
dc.contributor.author Randolph, Thomas
dc.contributor.author Sims, Jon
dc.contributor.author Timmerman, Paul
dc.date.accessioned 2015-07-14T18:06:23Z
dc.date.available 2015-07-14T18:06:23Z
dc.date.issued 2008-08-18
dc.identifier.citation AIAA/AAS Astrodynamics Specialist Conference, Honolulu, Hawaii, August 18-21, 2008 en_US
dc.identifier.clearanceno 08-2765
dc.identifier.uri http://hdl.handle.net/2014/45452
dc.description.abstract The disparate design problems of selecting an electric propulsion system, launch vehicle, and flight time all have a significant impact on the cost and robustness of a mission. The effects of these system choices combine into a single optimization of the total mission cost, where the design constraint is a required spacecraft neutral (non-electric propulsion) mass. Costoptimal systems are designed for a range of mass margins to examine how the optimal design varies with mass growth. The resulting cost-optimal designs are compared with results generated via mass optimization methods. Additional optimizations with continuous system parameters address the impact on mission cost due to discrete sets of launch vehicle, power, and specific impulse. The examined mission set comprises a near-Earth asteroid sample return, multiple main belt asteroid rendezvous, comet rendezvous, comet sample return, and a mission to Saturn. 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, 2008 en_US
dc.title Electric propulsion system selection process for interplanetary missions en_US
dc.type Preprint en_US


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