Fusion propulsion with the addition of indigenous gases
Conference
·
OSTI ID:5899106
A feasibility and performance projection study is conducted for a heavy-lift aerospace plane employing nuclear fusion propulsion in conjunction with the earth and Mars atmospheres indigenous gases, which allows a great simplification of propulsion system design and a similar reduction in vehicle mass. The estimated earth takeoff weight of the vehicle for this 250-day earth-Mars (round trip) interplanetary mission was 2500 mt, which resembles that of the lunar-mission Saturn 5 launcher; the estimated weight of the system when taking off from Mars for its return to earth was about 1200 mt. While N2 was the propellant for earth takeoff, that from Mars employed CO2. 26 refs.
- OSTI ID:
- 5899106
- Report Number(s):
- AIAA-Paper--93-2028; CONF-930633--
- Country of Publication:
- United States
- Language:
- English
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210600* -- Power Reactors
Auxiliary
Mobile Package
& Transportable
AMPLIFIERS
COST ESTIMATION
DESIGN
ELECTRONIC EQUIPMENT
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ION PROPULSION
LUNA SPACE PROBES
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RELIABILITY
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TECHNOLOGY ASSESSMENT
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