Nuclear propulsion for Mars exploration - Electric versus thermal

Details Nuclear propulsion for Mars exploration - Electric versus thermal Nuclear propulsion for Mars exploration - Electric versus thermal

Jul 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992jpnt.confqy...d&link_type=abstract

AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 28th, Nashville, TN, July 6-8, 1992. 12 p.

Computer Science

Performance

Manned Mars Missions, Nuclear Electric Propulsion, Round Trip Trajectories, Spacecraft Propulsion, Thrust Measurement, Interorbital Trajectories, Interplanetary Flight, Propulsion System Performance, Space Exploration

Scientific paper

Preliminary thrust balance measurements of efficiency with the Pulsed Inductive Thruster have shown that efficiencies of 40 to 50 percent may be achievable in the I(sp) range from 4000 to 6000 sec for a throttleable thruster in which I(sp) can be changed in flight by varying propellant injection valve pressure. Effectiveness of this thruster in providing support for Mars exploration missions is examined, with mission performance expressed in terms of initial mass in low earth orbit (IMLEO) as a function of trip time. Results are compared for an 'all-up' crew transfer vehicle and a lighter vehicle supported by a cargo vehicle that predelivers both return propellant, and a Mars taxi used for crew return to the Mars park orbit. The same mission comparison is made for an advanced nuclear thermal rocket. The all-up nuclear electric vehicle is found to save 25 days round-trip time compared to the nuclear thermal vehicle at the same IMLEO. The nuclear electric cargo vehicle reduces crew transfer time by 25 days for the same total mission mass. For the nuclear thermal vehicle, cargo predelivery reduces crew transfer time by 45 days, bringing it to within 5 days of the comparable nuclear electric vehicle round-trip time.

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