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Record Details

Record 7 of 18984
The open-cycle gas-core nuclear rocket engine - Some engineering considerations.
Author and Affiliation:
Taylor, M. F.
Whitmarsh, C. L., Jr.
Sirocky, P. J., Jr.
Iwanczyk, L. C.(NASA Lewis Research Center, Cleveland, Ohio, United States)
Abstract: A preliminary design study of a conceptual 6000-MW open-cycle gas-core nuclear rocket engine system was made. The engine has a thrust of 44,200 lb and a specific impulse of 4400 sec. The nuclear fuel is uranium-235 and the propellant is hydrogen. Critical fuel mass was calculated for several reactor configurations. Major components of the reactor (reflector, pressure vessel) and the waste heat rejection system were considered conceptually and were sized.
Publication Date: Jan 01, 1971
Document ID:
19720027681
(Acquired Dec 04, 1995)
Accession Number: 72A11347
Subject Category: NUCLEAR ENGINEERING
Document Type: Conference Proceedings
Publication Information: SEE A72-11326 01-22
Publisher Information: United States
Meeting Information: 2nd Symposium on Uranium Plasmas: Research and Applications; November 15-17, 1971; Atlanta, GA
Financial Sponsor: NASA; Unknown
Description: 10p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: GASEOUS ROCKET PROPELLANTS; NUCLEAR ROCKET ENGINES; REACTOR CORES; REACTOR DESIGN; ROCKET ENGINE DESIGN; CONFERENCES; CRITICAL MASS; GASEOUS FISSION REACTORS; HEAT RADIATORS; HYDROGEN; NUCLEAR FUELS; PRESSURE VESSEL DESIGN; SPECIFIC IMPULSE; THERMODYNAMIC CYCLES; URANIUM 235
Imprint And Other Notes: In: Symposium on Uranium Plasmas: Research and Applications, 2nd, Atlanta, Ga., November 15-17, 1971, Collection of Technical Papers (A72-11326 01-22) New York, American Institute of Aeronautics and Astronautics, Inc., 1971, p. 179-188.
Availability Source: Other Sources
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