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Title: Ultra-high temperature direct propulsion

Abstract

Potential advantages of ultra-high exhaust temperature (3000 K - 4000 K) direct propulsion nuclear rockets are explored. Modifications to the Particle Bed Reactor (PBR) to achieve these temperatures are described. Benefits of ultra-high temperature propulsion are discussed for two missions - orbit transfer (..delta..V = 5546 m/s) and interplanetary exploration (..delta..V = 20000 m/s). For such missions ultra-high temperatures appear to be worth the additional complexity. Thrust levels are reduced substantially for a given power level, due to the higher enthalpy caused by partial disassociation of the hydrogen propellant. Though technically challenging, it appears potentially feasible to achieve such ultra high temperatures using the PBR.

Authors:
; ; ;
Publication Date:
Research Org.:
Brookhaven National Lab., Upton, NY (USA)
OSTI Identifier:
6430200
Report Number(s):
BNL-39696; CONF-870102-24
ON: DE87010066
DOE Contract Number:  
AC02-76CH00016
Resource Type:
Conference
Resource Relation:
Conference: 4. symposium on space nuclear power systems, Albuquerque, NM, USA, 12 Jan 1987; Other Information: Portions of this document are illegible in microfiche products
Country of Publication:
United States
Language:
English
Subject:
21 SPECIFIC NUCLEAR REACTORS AND ASSOCIATED PLANTS; EFFICIENCY; TEMPERATURE DEPENDENCE; SPACE PROPULSION REACTORS; HYDROGEN; PERFORMANCE; PROPELLANTS; VERY HIGH TEMPERATURE; ELEMENTS; MOBILE REACTORS; NONMETALS; POWER REACTORS; PROPULSION REACTORS; REACTORS; SPACE POWER REACTORS; NESDPS Office of Nuclear Energy Space and Defense Power Systems; 220800* - Nuclear Reactor Technology- Propulsion Reactors

Citation Formats

Araj, K J, Slovik, G, Powell, J R, and Ludewig, H. Ultra-high temperature direct propulsion. United States: N. p., 1987. Web.
Araj, K J, Slovik, G, Powell, J R, & Ludewig, H. Ultra-high temperature direct propulsion. United States.
Araj, K J, Slovik, G, Powell, J R, and Ludewig, H. Thu . "Ultra-high temperature direct propulsion". United States. https://www.osti.gov/servlets/purl/6430200.
@article{osti_6430200,
title = {Ultra-high temperature direct propulsion},
author = {Araj, K J and Slovik, G and Powell, J R and Ludewig, H},
abstractNote = {Potential advantages of ultra-high exhaust temperature (3000 K - 4000 K) direct propulsion nuclear rockets are explored. Modifications to the Particle Bed Reactor (PBR) to achieve these temperatures are described. Benefits of ultra-high temperature propulsion are discussed for two missions - orbit transfer (..delta..V = 5546 m/s) and interplanetary exploration (..delta..V = 20000 m/s). For such missions ultra-high temperatures appear to be worth the additional complexity. Thrust levels are reduced substantially for a given power level, due to the higher enthalpy caused by partial disassociation of the hydrogen propellant. Though technically challenging, it appears potentially feasible to achieve such ultra high temperatures using the PBR.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1987},
month = {1}
}

Conference:
Other availability
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