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Revised Point of Departure Design Options for Nuclear Thermal PropulsionFour Revised Point of Departure NTR Engines were Designed and Analyzed using MCNP and NESS. All Four Engines Have Thermodynamically Closed Cycles at Nominal Chamber Pressures. 111 kilonewton (25 kip-force) Cermet Design Required Dedicated Heater Elements to Close the Cycle. Cermet Based Designs had Slightly Higher TW Ratios, but Required Substantially More U-235. NERVA Derived Criticality Limited Engine Could Operate at Lower Power and Thrust Levels Compared to the Criticality Limited Cermet Design.
Document ID
20150007681
Acquisition Source
Glenn Research Center
Document Type
Presentation
Authors
Fittje, James E. (Vantage Partners, LLC Brook Park, OH, United States)
Schnitzler, Bruce G. (Oak Ridge National Lab. TN, United States)
Borowoski, Stanley (NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
May 8, 2015
Publication Date
February 23, 2015
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
GRC-E-DAA-TN21157
Meeting Information
Meeting: Nuclear and Emerging Technologies for Space (NETS 2015)
Location: Albuquerque, NM
Country: United States
Start Date: February 23, 2015
End Date: February 26, 2015
Sponsors: Universities Space Research Association, American Nuclear Society, NASA Headquarters
Funding Number(s)
CONTRACT_GRANT: NNC12BA01B
WBS: WBS 279585.01.99.99.99.99.22
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Nuclear Thermal Rocket
Propulsion
Cycle Analysis

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