An Overview of Nuclear Thermal Propulsion Graphite, Composite, and CERMET Designs for Thrust Sizes 10,000 to 250,000-pounds

Joyner, Claude R.

doi:10.2514/6.2009-5237

Cited by 1 publication

(1 citation statement)

References 13 publications

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“…This is not the focus of this paper or study although the implications of the approach was examined for the scaled up 111 kN (25k-lbf) thrust size and was deemed feasible, especially with a derivative CERMET reactor core. (16,17,18,19,20) The small NTP demonstrator propulsion systems have the advantage of using technology that has already matured from legacy liquid rocket engines. Much of the propellant feed system, combustion chamber and nozzle section, the carbon-carbon nozzle extension, and the valves are available as hardware directly from engines like the PWR RL10 or the Advanced Upper Stage Engine components already tested.…”

Section: Table 1 -Summary Of Nerva-derived and Cermet Ntp Fuel Elemenmentioning

confidence: 99%

Development of a Small Nuclear Thermal Propulsion Flight Demonstrator Concept that Is Scalable to Human Missions

Joyner¹,

Levack²,

Borowski³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Recent exploration architectures are considering capability based approaches that use various propulsion technologies that need flight qualification. When human exploration missions come to fruition, rapidity of mission flight time and minimization of the number of flight elements will be important to reduce risk and cost. Nuclear thermal propulsion (NTP) is a technology that enables rapidity of transit and minimizes the number of spacecraft systems and launch vehicles to enable robust exploration. NTP has been proven scientifically and many engineering challenges have been addressed in past ground testing. The final validation and verification that still remains is to prove NTP in a flight demonstrator. Current efforts are focused on reducing demonstrator cost via application of proven liquid rocket components and fuel element design technology evolution.Pratt & Whitney Rocketdyne has been working with NASA Glenn Research Center to conceptualize the reactor design requirements and propulsion system design relative to a small NTP with scalability to human exploration spacecraft systems. Studies performed in 2011 and continuing through 2012 have defined the reactor neutronics, thermodynamic cycle, and component mass for a small NTP and the scalability of the design for larger (e.g., 25,000-lbf) propulsion systems. Part of these studies has shown this small NTP can be flight demonstrated using current Delta IV and Atlas V expendable launch vehicles and provide improved capability for robotic exploration missions. NomenclatureANL = Argonne National Lab BEO = Beyond Earth Orbit CERMET = CERamic-METallic matrix approach to Uranium-fueled Reactor Core Elements, Based on 710 Reactor Program of the USAEC, Contract No. AT (40-1)-2847 DoE = Department of Energy EOC = Earth Orbit Capture FOC = First (fully) Operational Capability EBAL = Engine BALance, Pratt & Whitney Rocketdyne parametric cycle design program GMAT = General Mission Analysis Tool, NASA GRC Open Source Trajectory Software GRC = Glenn Research Center, NASA Facility in Cleveland, Ohio ISP = Specific Impulse, a measure of efficiency (Thrust per pound of fuel burned), higher is better LEO = Low Earth Orbit LLO = Low Lunar Orbit LOI = Lunar Orbit Insertion NCPS = Nuclear Cryogenic Propulsion Stage NERVA = Nuclear Engine for Rocket Vehicle Applications NTP = Nuclear Thermal Propulsion RTAPS = Research and Technologies for Aerospace Propulsion Systems SAFE = Subsurface Active Filtering of Exhaust TLI = Trans-Lunar Injection TRL = Technology Readiness Level

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Section: Table 1 -Summary Of Nerva-derived and Cermet Ntp Fuel Elemenmentioning

confidence: 99%

Development of a Small Nuclear Thermal Propulsion Flight Demonstrator Concept that Is Scalable to Human Missions

Joyner¹,

Levack²,

Borowski³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

Self Cite

View full text Add to dashboard Cite

show abstract

An Overview of Nuclear Thermal Propulsion Graphite, Composite, and CERMET Designs for Thrust Sizes 10,000 to 250,000-pounds

Cited by 1 publication

References 13 publications

Development of a Small Nuclear Thermal Propulsion Flight Demonstrator Concept that Is Scalable to Human Missions

Development of a Small Nuclear Thermal Propulsion Flight Demonstrator Concept that Is Scalable to Human Missions

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