SP-100 nuclear electric propulsion for Mars cargo missions

Details SP-100 nuclear electric propulsion for Mars cargo missions SP-100 nuclear electric propulsion for Mars cargo missions

Jun 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993jpmc.confu....f&link_type=abstract

AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, 1993, 23 p.

Computer Science

Performance

Cargo Spacecraft, Interplanetary Flight, Magnetoplasmadynamics, Mars Landing, Nuclear Electric Propulsion, Lunar Flight, Manned Mars Missions, Mars Probes, Mission Planning, Rankine Cycle, Rocket Engine Design

Scientific paper

This paper summarizes an evaluation of mission performance (in terms of vehicle mass and trip time) of the use of the near-term SP-100 reactor technology for nuclear electric propulsion for Mars cargo missions, and of the technology requirements for the propulsion and dynamic power conversion systems of the vehicle. The reactor power system uses dynamic power conversion (Rankine), and the propulsion system uses lithium-propellant magnetoplasmadynamic (MPD) thrusters. Three reactor power modules are used to give a total 'bus' power of 1.7 MWe. The total power, power conditioning, and propulsion systems specific mass is 24.8 kg/kWe; the propellant tankage factor is 2.8 percent. The power conditioning system has an efficiency of 90.2 percent and the MPD thrusters an efficiency (electric-to-jet) of 60 percent at a nominal specific impulse of 5000 lb(f)-s/lb(m). Rankine, Brayton, and Stirling dynamic power conversion systems were compared, and the Rankine was found to give the best performance in terms of smallest specific mass and volume; however, it has the longest development time requirement.

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