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A review of nuclear electric propulsion spacecraft system conceptsThe last 25-30 years of system concepts and design philosophies for spacecraft employing nuclear-electric propulsion (NEP) are reviewed. NEP spacecraft-system design constraints and criteria are identified, including radiation exposure of humans and electronics, thermal control requirements, effluent contamination of spacecraft surfaces, surface erosion, launch-vehicle integration, operations and safety requirements, attitude control, EM interference, and power control and distribution. The impact on spacecraft design philosophy of these constraints and criteria is explored. Several NEP spacecraft are characterized and discussed with respect to the propulsion system used. The electric propulsion system catagories are electrothermal (arcjet), EM (magnetoplasmadynamic and pulsed-inductive thruster) and electrostatic (ion engine). A brief summary of the mission, nuclear power source, electric propulsion system, and spacecraft configuration are provided for each NEP spacecraft concept.
Document ID
19900055489
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Deininger, W. D.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Nock, K. T.
(JPL Pasadena, CA, United States)
Date Acquired
August 14, 2013
Publication Date
July 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-2553
Accession Number
90A42544
Distribution Limits
Public
Copyright
Other

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