A comparison of propulsion systems for potential space mission applications
A derivative of the NERVA nuclear rocket engine was compared with a chemical propulsion system and a nuclear electric propulsion system to assess the relative capabilities of the different propulsion system options for three potential space missions. The missions considered were (1) orbital transfer from low earth orbit (LEO) to geosynchronous earth orbit (GEO), (2) LEO to a lunar base, and (3) LEO to Mars. The results of this comparison indicate that the direct-thrust NERVA-derivative nuclear rocket engine has the best performance characteristics for the missions considered. The combined high thrust and high specific impulse achievable with a direct-thrust nuclear stage permits short operating times (transfer times) comparable to chemical propulsion systems, but with considerably less required propellant. While nuclear-electric propulsion systems are more fuel efficient than either direct-nuclear or chemical propulsion, they are not stand-alone systems, since their relatively low thrust levels require the use of high-thrust ferry or lander stages in high gravity applications such as surface-to-orbit propulsion. The extremely long transfer times and inefficient trajectories associated with electric propulsion systems were also found to be a significant drawback.
- Research Organization:
- EG and G Idaho, Inc., Idaho Falls (USA); Martin Marietta Corp., Englewood, CO (USA)
- DOE Contract Number:
- AC07-76ID01570
- OSTI ID:
- 5654347
- Report Number(s):
- EGG-M-38287; CONF-871234-12; ON: DE88005637
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
220800* -- Nuclear Reactor Technology-- Propulsion Reactors
COMPARATIVE EVALUATIONS
DESIGN
MOBILE REACTORS
NESDPS Office of Nuclear Energy Space and Defense Power Systems
PERFORMANCE
POWER REACTORS
PROPULSION REACTORS
PROPULSION SYSTEMS
REACTORS
SPACE POWER REACTORS
SPACE PROPULSION REACTORS