Nuclear powered Mars cargo transport mission utilizing advanced ion propulsion

Conference · Thu Jan 01 00:00:00 EST 1987

OSTI ID:5983122

Galecki, D L; Patterson, M J

Nuclear-powered ion propulsion technology was combined with detailed trajectory analysis to determine propulsion system and trajectory options for an unmanned cargo mission to Mars in support of manned Mars missions. A total of 96 mission scenarios were identified by combining two power levels, two propellants, four values of specific impulse per propellant, three starting altitudes, and two starting velocities. Sixty of these scenarios were selected for a detailed trajectory analysis; a complete propulsion system study was then conducted for 20 of these trajectories. Trip times ranged from 344 days for a xenon propulsion system operating at 300 kW total power and starting from lunar orbit with escape velocity, to 770 days for an argon propulsion system operating at 300 kW total power and starting from nuclear start orbit with circular velocity. Trip times for the 3 MW cases studied ranged from 356 to 413 days. Payload masses ranged from 5700 to 12,300 kg for the 300 kW power level, and from 72,200 to 81,500 kg for the 3 MW power level.

• Research Organization: National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
• OSTI ID: 5983122
• Report Number(s): N-87-23692; NASA-TM-100109; E-3641; NAS-1.15:100109; AIAA-87-1903; CONF-8706157-5
• Resource Relation: Conference: 23. AIAA/SAE/ASME/ASEE joint propulsion conference, San Diego, CA, USA, 29 Jun 1987
• Country of Publication: United States
• Language: English

Related Subjects

21 SPECIFIC NUCLEAR REACTORS AND ASSOCIATED PLANTS
MARS PLANET
MISSION ANALYSIS
SPACE PROPULSION REACTORS
SPACE VEHICLES
ION PROPULSION
PROPELLANTS
MOBILE REACTORS
PLANETS
POWER REACTORS
PROPULSION
PROPULSION REACTORS
REACTORS
SPACE POWER REACTORS
VEHICLES
NESDPS Office of Nuclear Energy Space and Defense Power Systems
220800* - Nuclear Reactor Technology- Propulsion Reactors