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SEP Mission Design Space for Mars OrbitersThe advancement of solar-electric propulsion (SEP) technologies and larger, light-weight solar arrays offer a tremendous advantage to Mars orbiters in terms of both mass and timeline flexibility. These advantages are multiplied for round-trip orbiters (e.g. potential Mars sample return) where a large total Delta V would be required. In this paper we investigate the mission design characteristics of mission concepts utilizing various combinations and types of SEP thrusters, solar arrays, launch vehicles, launch dates, arrival dates, etc. SEP allows for greater than 50% more mass delivered and launch windows of months to years. We also present the SEP analog to the ballistic Porkchop plot - the "Bacon" plot.
Document ID
20170008222
Document Type
Conference Paper
External Source(s)
Authors
Woolley, Ryan C.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Nicholas, Austin K.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
September 1, 2017
Publication Date
August 9, 2015
Subject Category
Spacecraft Design, Testing And Performance
Meeting Information
AAS/AIAA Astrodynamics Specialist Conference(Vail, CO)
Distribution Limits
Public
Copyright
Other
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