Arcjet propulsion system for an SP-100 flight experiment
The design and performance of a arcjet nuclear electric propulsion spacecraft, suitable for use in a space reactor power system (SRPS) flight experiment, are outlined. The vehicle design is based on a 92-kW ammonia arcjet system operating at a specific impulse of 1050 s and an efficiency of 45 percent. The arcjet/gimbal system, power processing unit, and propellant feed system are described. A 100-kW SRPS is assumed and the spacecraft mass is baselined at 5250 kg, excluding the propellant and propellant feed system. A radiation/arcjet efflux diagnostics package is included in the performance analysis. This spacecraft, assuming a Shuttle launch from Kennedy Space Center, can perform a 35-deg inclination change and reach a final orbit of 35,860 km with a 120-day trip time, thus providing a four-month active load for the SRPS. Alternatively, a Titan IV launch could provide a mass margin of 120 kg to a 1000km, 58-deg final orbit in 74 days. 38 references.
- Research Organization:
- California Institute of Technology, Pasadena (USA); W. J. Schafer Associates, Inc., Arlington, VA (USA)
- OSTI ID:
- 6288464
- Journal Information:
- J. Spacecr. Rockets; (United States), Journal Name: J. Spacecr. Rockets; (United States) Journal Issue: 6 Vol. 25; ISSN JSCRA
- Country of Publication:
- United States
- Language:
- English
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