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Ground Test Technology Demonstration for Nuclear Thermal Propulsion EnginesNuclear Thermal Propulsion (NTP) engines have been deemed a key technology to enable human missions to Mars due to their high efficiency, also known as specific impulse (Isp). Ground testing the NTP engine is critical in maturing the technology and increasing the design’s Technology Readiness Level (TRL), thus mitigating risk from NTP engine performance/operations. NTP engine development began with open-air ground testing through the Rover/NERVA program back in the 1960s when regulatory requirements were not as stringent as they are today. Due to the formation of regulatory bodies, increase in oversight and environmental requirements, the exhaust gas released from NTP engines must be captured or processed to gain approval in the case that the exhaust gas contains fission products from the nuclear fuel elements within the reactor. Ground test campaigns following Rover/NERVA focused on the certification of a full scale NTP engine, which led to exhaust processing systems such as the Rocket Exhaust Capture System (RECS) and Real Time (RT) exhaust processing. These systems were deemed favorable for regulatory compliance but have a high initial investment cost. Reassurance on the feasibility of ground testing and the NTP engine technology likely need to be achieved before NASA invests in these systems. Recently the objectives for NTP engine ground testing have shifted from certification testing of a full scale engine to demonstration testing of a subscale engine. The shift to demonstration testing allows for a shorter testing duration and a lower operational thrust (for demo testing purposes only) to demonstrate the NTP engine (5k-12.5k lbf). Due to these factors, the infrastructure, consumables, total footprint, and exhaust system complexity are able to be drastically reduced, thus reducing cost significantly. The High-pressure Exhaust Capture System (HECS) concept was designed for a NTP engine ground test demonstration. The HECS concept greatly reduces cost compared to previous concepts and suggests favorable regulatory acceptance due to its ability to capture all of the exhaust gas from the NTP engine.
Document ID
20230003170
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Ricky Sasmal
(Analytical Mechanics Associates (United States) Hampton, Virginia, United States)
Lindsey Holmes
(Analytical Mechanics Associates (United States) Hampton, Virginia, United States)
Jim Rector
(Analytical Mechanics Associates (United States) Hampton, Virginia, United States)
Marcus Neely
(Jacobs (United States) Dallas, Texas, United States)
Date Acquired
March 8, 2023
Subject Category
Spacecraft Propulsion and Power
Lunar and Planetary Science and Exploration
Meeting Information
Meeting: Nuclear and Emerging Technologies for Space (NETS)
Location: Idaho Falls, ID
Country: US
Start Date: May 7, 2023
End Date: May 11, 2023
Sponsors: American Nuclear Society
Funding Number(s)
CONTRACT_GRANT: 80LARC17C0003
Distribution Limits
Public
Copyright
Public Use Permitted.
Technical Review
Professional Review
Keywords
Nuclear Thermal Propulsion
Engine
Ground Demonstration Testing
Manned Mission to Mars
Exhaust Capture
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