Neutronics Models and Analysis of the Small Nuclear Rocket Engine (SNRE)

Schnitzler, Bruce G.; Borowski, Stanley K.

doi:10.2514/6.2007-5618

Cited by 20 publications

(12 citation statements)

References 1 publication

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“…The core design follows the standard NTR configuration originally proposed by the NERVA program and later refined by researchers at Los Alamos National Laboratory, Idaho National Laboratory, and various NASA research groups (Division, 1969;Durham, 1972;Schnitzler and Borowski, 2007). The core configuration consists of an active core region and a reflector region surrounding the active core on three sides, leaving the core exit open to the nozzle.…”

Section: Core Descriptionmentioning

confidence: 99%

A feasibility study on low enriched uranium fuel for nuclear thermal rockets – II: Rocket and reactor performance

Venneri

Kim

2016

Progress in Nuclear Energy

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Section: Core Descriptionmentioning

confidence: 99%

A feasibility study on low enriched uranium fuel for nuclear thermal rockets – II: Rocket and reactor performance

Venneri

Kim

2016

Progress in Nuclear Energy

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“…Geometry and material data for the external components are documented in Table 6 of Ref. 5. The model extends axially from the aft end of the active fuel forward through the internal shields.…”

Section: A Mcnp Models and Methodsmentioning

confidence: 99%

“…Initial efforts were focused on benchmarking methods and models against the Small Nuclear Rocket Engine (SNRE) and stage configuration documented in the Nuclear Engine Definition Study (NEDS) Preliminary reports 3,4 . Past papers have addressed neutronics modeling of the SNRE reactor core 5 , the SNRE reference stage 6 , integrated thermal-fluid-structural analysis of reactor core interior components 7 , engine system level modeling and analyses 8 , and an extension of the SNRE design into the 25,000 lbf thrust range 9 . Most nuclear thermal propulsion engine designs utilize uranium fuel enriched to 93 wt% 235 U.…”

Section: Introductionmentioning

confidence: 99%

Enrichment Zoning Options for the Small Nuclear Rocket Engine (SNRE)

Schnitzler¹,

Borowski²

2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Engine Conceptual Design, Analysis, and Modeling aimed at developing conceptual designs of small demonstration engines and the full size 25 klb f -class engines utilizing the candidate fuels discussed above. State-of-theart numerical models will be used to determine reactor core criticality, detailed energy deposition and control rod worth within the reactor subsystem [18], provide thermal, fluid and stress analysis of fuel element geometries [19], and predict engine operating characteristics and overall mass [20]; Task 4. Demonstration of Affordable Ground Testing focused on "proof-of-concept" validation of the SAFE (Subsurface Active Filtration of Exhaust) [21] or "borehole" test option at the Nevada Test Site (NTS).…”

Section: Plans For Ntp Technology Development and Demonstrationmentioning

confidence: 99%

Nuclear Thermal Propulsion (NTP): A proven growth technology for human NEO/Mars exploration missions

Borowski

McCurdy²,

Packard

2012

2012 IEEE Aerospace Conference

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Abstract-The nuclear thermal rocket (NTR) represents the next "evolutionary step" in high performance rocket propulsion. Unlike conventional chemical rockets that produce their energy through combustion, the NTR derives its energy from fission of Uranium-235 atoms contained within fuel elements that comprise the engine's reactor core. Using an "expander" cycle for turbopump drive power, hydrogen propellant is raised to a high pressure and pumped through coolant channels in the fuel elements where it is superheated then expanded out a supersonic nozzle to generate high thrust. By using hydrogen for both the reactor coolant and propellant, the NTR can achieve specific impulse (I sp ) values of ~900 seconds (s) or more -twice that of today's best chemical rockets. From 1955From -1972, twenty rocket reactors were designed, built and ground tested in the Rover and NERVA (Nuclear Engine for Rocket Vehicle Applications) programs. These programs demonstrated: (1) high temperature carbide-based nuclear fuels; (2) a wide range of thrust levels; (3) sustained engine operation; (4) accumulated lifetime at full power; and (5) restart capability -all the requirements needed for a human Mars mission. Ceramic metal "cermet" fuel was pursued as well, as a backup option. The NTR also has significant "evolution and growth" capability. Configured as a "bimodal" system, it can generate its own electrical power to support spacecraft operational needs. Adding an oxygen "afterburner" nozzle introduces a variable thrust and I sp capability and allows bipropellant operation. In NASA's recent Mars Design Reference Architecture (DRA) 5.0 study, the NTR was selected as the preferred propulsion option because of its proven technology, higher performance, lower launch mass, versatile vehicle design, simple assembly, and growth potential. In contrast to other advanced propulsion options, no large technology scale-ups are required for NTP either. In fact, the smallest engine tested during the Rover program -the 25,000 lb f (25 klb f ) "Pewee" engine is sufficient when used in a clustered engine arrangement. The "Copernicus" crewed spacecraft design developed in DRA 5.0 has significant capability and a human exploration strategy is outlined here that uses Copernicus and its key components for precursor near Earth object (NEO) and Mars orbital missions prior to a Mars landing mission. The paper also discusses NASA's current activities and future plans for NTP development that include system-level Technology Demonstrations -specifically ground testing a small, scalable NTR by 2020, with a flight test shortly thereafter.

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Neutronics Models and Analysis of the Small Nuclear Rocket Engine (SNRE)

Cited by 20 publications

References 1 publication

A feasibility study on low enriched uranium fuel for nuclear thermal rockets – II: Rocket and reactor performance

A feasibility study on low enriched uranium fuel for nuclear thermal rockets – II: Rocket and reactor performance

Enrichment Zoning Options for the Small Nuclear Rocket Engine (SNRE)

Nuclear Thermal Propulsion (NTP): A proven growth technology for human NEO/Mars exploration missions

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