Electric propulsion options for the SP-100 reference mission
Analyses were performed to characterize and compare electric propulsion systems for use on a space flight demonstration of the SP-100 nuclear power system. The component masses of resistojet, arcjet, and ion thruster systems were calculated using consistent assumptions and the maximum total impulse, velocity increment, and thrusting time were determined, subject to the constraint of the lift capability of a single Space Shuttle launch. From the study it was found that for most systems the propulsion system dry mass was less than 20 percent of the available mass for the propulsion system. The maximum velocity increment was found to be up to 2890 m/sec for resistojet, 3760 m/sec for arcjet, and 23 000 m/sec for ion thruster systems. The maximum thruster time was found to be 19, 47, and 853 days for resistojet, arcjet, and ion thruster systems, respectively.
- Research Organization:
- National Aeronautics and Space Administration, Cleveland, OH (USA). Lewis Research Center
- OSTI ID:
- 6815926
- Report Number(s):
- N-87-14422; NASA-TM-88918; E-3343; NAS-1.15:88918; CONF-870102-11
- Country of Publication:
- United States
- Language:
- English
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DATA
INFORMATION
ION PROPULSION
MASS
MOBILE REACTORS
NESDPS Office of Nuclear Energy Space and Defense Power Systems
NUMERICAL DATA
POWER REACTORS
PROPULSION
PROPULSION SYSTEMS
REACTORS
SPACE POWER REACTORS
SPECIFICATIONS
THEORETICAL DATA
THRUSTERS