Nuclear thermal rockets using indigenous Martian propellants
Conference
·
OSTI ID:5523246
This paper considers a novel concept for a Martian descent and ascent vehicle, called NIMF (for nuclear rocket using indigenous Martian fuel), the propulsion for which will be provided by a nuclear thermal reactor which will heat an indigenous Martian propellant gas to form a high-thrust rocket exhaust. The performance of each of the candidate Martian propellants, which include CO2, H2O, CH4, N2, CO, and Ar, is assessed, and the methods of propellant acquisition are examined. Attention is also given to the issues of chemical compatibility between candidate propellants and reactor fuel and cladding materials, and the potential of winged Mars supersonic aircraft driven by this type of engine. It is shown that, by utilizing the nuclear landing craft in combination with a hydrogen-fueled nuclear thermal interplanetary vehicle and a heavy lift booster, it is possible to achieve a manned Mars mission in one launch. 6 refs.
- OSTI ID:
- 5523246
- Report Number(s):
- AIAA-Paper--89-2768; CONF-8907118--
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
42 ENGINEERING
420200* -- Engineering-- Facilities
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& Techniques
70 PLASMA PHYSICS AND FUSION TECHNOLOGY
700200 -- Fusion Energy-- Fusion Power Plant Technology
DESIGN
ENGINES
ENVIRONMENT
EXPLORATION
MARS PLANET
NESDPS Office of Nuclear Energy Space and Defense Power Systems
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PROPELLANTS
PROPULSION SYSTEMS
ROCKET ENGINES
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420200* -- Engineering-- Facilities
Equipment
& Techniques
70 PLASMA PHYSICS AND FUSION TECHNOLOGY
700200 -- Fusion Energy-- Fusion Power Plant Technology
DESIGN
ENGINES
ENVIRONMENT
EXPLORATION
MARS PLANET
NESDPS Office of Nuclear Energy Space and Defense Power Systems
PLANETS
PROPELLANTS
PROPULSION SYSTEMS
ROCKET ENGINES
SPACE VEHICLES
THERMONUCLEAR REACTORS
VEHICLES