Design and performance of an arcjet nuclear electric propulsion system for a mid-1990's reference mission
The design and performance of an arcjet nuclear-electric-propulsion spacecraft, suitable for use in the Space Nuclear Power System (SNPS) reference mission, are outlined. The vehicle design was based on a 30-kW ammonia arcjet system operating at an Isp of 1050 s and an efficiency of 45 percent. The arcjet/gimbal system, power-processing unit, and propellant-feed system are described. A 100-kWe SNPS was assumed, and the spacecraft mass was baselined at 5250 kg (excluding the propellant-feed system). A radiation/arcjet efflux diagnostics package was included in the performance analysis. This spacecraft, assuming a Shuttle launch from KSC, can perform a 50-deg inclination change and reach a final orbit of 35,860 km with a 120-d trip time providing a 4-mo active load for the SNPS. Alternatively, a Titan IV launch would provide a mass margin of 120 kg to a 10,000-km, 58-deg final orbit in 74 d. This spacecraft meets the reference-mission constraint of low developmental risk, and is scalable to power levels projected for future space platforms. 36 references.
- Research Organization:
- California Institute of Technology, Pasadena; USAF, Rocket Propulsion Laboratory, Edwards AFB, CA
- OSTI ID:
- 6244685
- Report Number(s):
- AIAA-Paper-8-1037; CONF-870558-
- Journal Information:
- AIAA Pap.; (United States), Journal Name: AIAA Pap.; (United States); ISSN AAPRA
- Country of Publication:
- United States
- Language:
- English
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