Chemical and Solar-Electric-Propulsion Systems Analyses for Mars Sample Return Missions | Zendy

Benjamin Donahue | Zendy; Shaun E. Green | Zendy; Victoria Coverstone | Zendy; Byoungsam Woo | Zendy

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Chemical and Solar-Electric-Propulsion Systems Analyses for Mars Sample Return Missions

Author(s) -

Benjamin Donahue,

Shaun E. Green,

Victoria Coverstone,

Byoungsam Woo

Publication year - 2006

Publication title -

journal of spacecraft and rockets

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.758

H-Index - 79

eISSN - 1533-6794

pISSN - 0022-4650

DOI - 10.2514/1.13958

Subject(s) - aerospace engineering , in space propulsion technologies , spacecraft , mars exploration program , propulsion , spacecraft design , systems engineering , space exploration , missile , space (punctuation) , spacecraft propulsion , space research , astrobiology , space environment , electrically powered spacecraft propulsion , exploration of mars , space technology , engineering , computer science , physics , geophysics , operating system

Conceptual in-space transfer stages, including those utilizing solar electric propulsion, chemical propulsion, and chemical propulsion with aerobraking or aerocapture assist at Mars, were evaluated. Roundtrip Mars sample return mission vehicles were analyzed to determine how specific system technology selections influence payload delivery capability. Results show how specific engine, thruster, propellant, capture mode, trip time and launch vehicle technology choices would contribute to increasing payload or decreasing the size of the required launch vehicles. Heliocentric low-thrust trajectory analyses for Solar Electric Transfer were generated with the SEPTOP code.

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