Nuclear vapor thermal reactor propulsion technology

Conference · Wed Jan 20 04:00:00 EST 1993 · AIP Conference Proceedings (American Institute of Physics); (United States)

DOI:https://doi.org/10.1063/1.43056· OSTI ID:5460580

Maya, I; Diaz, N J; Dugan, E T; Watanabe, Y ^[1]; McClanahan, J A; Tu, Wen-Hsiung; Carman, R L ^[2]

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1. Innovative Nuclear Space Power and Propulsion Institute, University of Florida, Gainesville, Florida 32611 (United States)
2. Rocketdyne Division/Rockwell International Corporation, P.O. Box 7922, Canoga Park, California 91309-7922 (United States)

The conceptual design of a nuclear rocket based on the vapor core reactor is presented. The Nuclear Vapor Thermal Rocket (NVTR) offers the potential for a specific impulse of 1000 to 1200 s at thrust-to-weight ratios of 1 to 2. The design is based on NERVA geometry and systems with the solid fuel replaced by uranium tetrafluoride (UF[sub 4]) vapor. The closed-loop core does not rely on hydrodynamic confinement of the fuel. The hydrogen propellant is separated from the UF[sub 4] fuel gas by graphite structure. The hydrogen is maintained at high pressure ([similar to]100 atm), and exits the core at 3,100 K to 3,500 K. Zirconium carbide and hafnium carbide coatings are used to protect the hot graphite from the hydrogen. The core is surrounded by beryllium oxide reflector. The nuclear reactor core has been integrated into a 75 klb engine design using an expander cycle and dual turbopumps. The NVTR offers the potential for an incremental technology development pathway to high performance gas core reactors. Since the fuel is readily available, it also offers advantages in the initial cost of development, as it will not require major expenditures for fuel development.

• OSTI ID: 5460580
• Report Number(s): CONF-930103--
• Conference Information: Journal Name: AIP Conference Proceedings (American Institute of Physics); (United States) Journal Volume: 271:3
• Country of Publication: United States
• Language: English

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