Neutronic analysis methodology and results are presented for the nuclear design of a vapor core reactor for space nuclear propulsion. The Nuclear Vapor Thermal Reactor (NVTR) Rocket Engine uses modified NERVA geometry and systems which the solid fuel replaced by uranium tetrafluoride vapor. The NVTR is an intermediate term gas core thermal rocket engine with specific impulse in the range of 1000–1200 seconds; a thrust of 75,000 lbs for a hydrogen flow rate of 30 kg/s; average core exit temperatures of 3100 K to 3400 K; and reactor thermal powers of 1400 to 1800 MW. Initial calculations were performed on epithermal NVTRs using ZrC fuel elements. Studies are now directed at thermal NVTRs that use fuel elements made of C‐C composite. The large ZrC‐moderated reactors resulted in thrust‐to‐weight ratios of only 1 to 2; the compact C‐C composite systems yield thrust‐to‐weight ratios of 3 to 5.
Nuclear design of a vapor core reactor for space nuclear propulsion
10th SymposiumùSpace Nuclear Power and Propulsion ; 1993 ; Albuquerque, NM, USA
AIP Conference Proceedings ; 271 , 2 ; 655-662
1993-01-15
8 pages
Conference paper
Electronic Resource
English
Nuclear Design of a Vapor Core Reactor for Space Nuclear Propulsion
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