Nuclear propulsion—a historical perspective

Gunn, S. V.

doi:10.1016/s0265-9646(01)00044-3

Cited by 20 publications

(2 citation statements)

References 11 publications

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“…This fuel type was formed into solid plates allowing the hydrogen propellant to pass over Gained from the Space Nuclear Rocket Program (Rover)" [6], [9], [10]. The all carbide fuel matrix was first tested in the NF-1 engine, meaning the tworecord holding engines of the Phoebus-2A and the Pewee both use the less durable uranium dicarbide fuel.…”

Section: Theory Of An Aerospike Nozzlementioning

confidence: 99%

Nuclear Thermal Rocket Engine with a Toroidal Aerospike Nozzle

Stewart

Papadopoulos

Pollard

2020

AIAA Propulsion and Energy 2020 Forum

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Section: Theory Of An Aerospike Nozzlementioning

confidence: 99%

Nuclear Thermal Rocket Engine with a Toroidal Aerospike Nozzle

Stewart

Papadopoulos

Pollard

2020

AIAA Propulsion and Energy 2020 Forum

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“…The KIWI reactors of the Los Alamos Scientific Laboratory (LASL) and the Tory reactors of the Lawrence Livermore Laboratories used ammonia and nitrogen, respectively. The Rocketdyne Division of North American Aviation identified hydrogen as a more suitable propellant than ammonia and nitrogen [1].…”

Section: Introductionmentioning

confidence: 99%

Modeling Loss-of-Flow Accidents and Their Impact on Radiation Heat Transfer

Khatry

Aydoğan

2017

Science and Technology of Nuclear Installations

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Long-term high payload missions necessitate the need for nuclear space propulsion. The National Aeronautics and Space Administration (NASA) investigated several reactor designs from 1959 to 1973 in order to develop the Nuclear Engine for Rocket Vehicle Application (NERVA). Study of planned/unplanned transients on nuclear thermal rockets is important due to the need for long-term missions. In this work, a system model based on RELAP5 is developed to simulate loss-of-flow accidents on the Pewee I test reactor. This paper investigates the radiation heat transfer between the fuel elements and the structures around it. In addition, the impact on the core fuel element temperature and average core pressure was also investigated. The following expected results were achieved: (i) greater than normal fuel element temperatures, (ii) fuel element temperatures exceeding the uranium carbide melting point, and (iii) average core pressure less than normal. Results show that the radiation heat transfer rate between fuel elements and cold surfaces increases with decreasing flow rate through the reactor system. However, radiation heat transfer decreases when there is a complete LOFA. When there is a complete LOFA, the peripheral coolant channels of the fuel elements handle most of the radiation heat transfer. A safety system needs to be designed to counteract the decay heat resulting from a post-LOFA reactor scram.

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Propulsion Systems

Moss

Stark

2011

Spacecraft Systems Engineering

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Nuclear propulsion—a historical perspective

Cited by 20 publications

References 11 publications

Nuclear Thermal Rocket Engine with a Toroidal Aerospike Nozzle

Nuclear Thermal Rocket Engine with a Toroidal Aerospike Nozzle

Modeling Loss-of-Flow Accidents and Their Impact on Radiation Heat Transfer

Propulsion Systems

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