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a comparison of electric propulsion systems for mars explorationEarth-Mars trajectories for multiple solar-powered spacecraft configurations were generated using Hall and ion propulsion systems utilizing the Direct Trajectory Optimization Method. Payload and power trades versus trip time were examined. Performance was compared for purely interplanetary flight and interplanetary flight with estimated spiral in to Mars orbit. Evaluating current ion and Hall thruster technologies, similar payload masses were delivered by each at equivalent trip times, but with the Hall thruster operating at a power level 10 kilowatts, on average, less than the ion thruster. The power difference for equivalent payload delivered should result in a significant cost savings.
Document ID
20030105665
Document Type
Technical Memorandum (TM)
Authors
Fiehler, Douglas
(QSS Group, Inc. Cleveland, OH, United States)
Oleson, Steve
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
September 1, 2003
Subject Category
Astrodynamics
Report/Patent Number
NAS 1.15:212593
AIAA Paper 2003-4574
E-14150
NASA/TM-2003-212593
Meeting Information
39th Joint Propulsion Conference and Exhibit(Huntsville, AL)
Funding Number(s)
WBS: WBS 22-982-10-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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