Mixed NEP/NTP propulsion for split Mars missions

Conference · Sat Jan 09 23:00:00 EST 1993 · AIP Conference Proceedings (American Institute of Physics); (United States)

DOI:https://doi.org/10.1063/1.43247· OSTI ID:5588372

Stancati, M L; McAdams, J V; Collins, J T ^[1]

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1. Science Applications International Corporation, 1515 Woodfield Road, Suite 350, Schaumburg, Illinois 60173 (United States)

Speed and safety have emerged as key factors in preliminary designs for piloted missions to Mars. Mission planners seek short flight times to maximize productive exploration time, and to minimize the risk of extended periods in space. To meet these objectives with reasonably sized vehicles will require some form of advanced propulsion; if the choice is nuclear, additional safety constraints may apply. Element-level redundancy for crew safety requires a significant increase in propulsion capability to keep vehicle and propellant masses within reason. Mixed high/low thrust propulsion for split Mars missions is a high performance option that supports fast, safe crew transfers, large payload movement, disposal of spent reactors, and feasible vehicle sizing throughout.

• OSTI ID: 5588372
• Report Number(s): CONF-930103--
• Journal Information: AIP Conference Proceedings (American Institute of Physics); (United States), Journal Name: AIP Conference Proceedings (American Institute of Physics); (United States) Vol. 271:1; ISSN 0094-243X; ISSN APCPCS
• Country of Publication: United States
• Language: English

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