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Feasibility of rotating fluidized bed reactor for rocket propulsionThe rotating fluidized bed reactor concept is outlined, and its application to rocket propulsion is discussed. Experimental results obtained indicate that minimum fluidization correlations commonly in use for 1-g beds can also be applied to multiple-g beds. It was found that for a low thrust system (20,000 lbf) the fuel particle size and/or particle stress play a limiting role on performance. The superiority of U-233 as a fuel for this type of rocket engine is clearly demonstrated in the analysis. The maximum thrust/weight ratio for a 90,000N thrust engine was found to be approximately 65N/kg.
Document ID
19740038642
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Ludewig, H.
Manning, A. J.
Raseman, C. J.
(Brookhaven National Laboratory Upton, N.Y., United States)
Date Acquired
August 7, 2013
Publication Date
February 1, 1974
Publication Information
Publication: Journal of Spacecraft and Rockets
Volume: 11
Subject Category
Nuclear Engineering
Accession Number
74A21392
Distribution Limits
Public
Copyright
Other

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