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- "The Nuclear Thermal Rocket Element Environmental Simulator" test section closely simulates the internal operating conditions of a thermal nuclear rocket. The purpose of testing is to determine the ideal fuel rod characteristics for optimum thermal heat transfer to their hydrogen cooling/working fluid while still maintaining fuel rod structural integrity. Working fluid exhaust temperatures of up to 5,000 degrees Fahrenheit can be encountered. The exhaust gas is rendered inert and massively reduced in temperature for analysis using a combination of water cooling channels and cool N2 gas injectors in the H2-N2 mixer portion of the test section. An extensive thermal fluid analysis was performed in support of the engineering design of the H2-N2 mixer in order to determine the maximum "mass flow rate"-"operating temperature" curve of the fuel elements hydrogen exhaust gas based on the test facilities available cooling N2 mass flow rate as the limiting factor.
- Other Subject(s):
- NASA Technical Reports Server (NTRS) Collection.
- Document ID: 20120002965.
JANNAF 8th Modeling and Simulation Subcommittee Meeting; 5-9 Dec. 2011; Huntsville, AL; United States.
JANNAF 5th Spacecraft Propulsion Subcommittee Meeting; 5-9 Dec. 2011; Huntsville, AL; United States.
JANNAF 6th Liquid Propulsion Subcommittee Meeting; 5-9 Dec. 2011; Huntsville, AL; United States.
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