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Title: Plasma core nuclear rocket technology

Abstract

The nuclear lightbulb (NLB) rocket propulsion concept furnishes specific impulse above 2000 sec in conjunction with the greater-than-50,000 lb thrust levels required for rapid transit-time round-trip Mars missions requiring low initial mass in earth orbit. The NLB transfers energy from the gaseous nuclear fuel region to a hydrogen propellant via thermal radiation, thereby precluding material temperature constraints. An evaluation is presently made of technology and test method readiness for implementation and validation of this propulsion system concept. 13 refs.

Authors:
; ;
Publication Date:
OSTI Identifier:
5855415
Report Number(s):
AIAA-Paper-93-2004; CONF-930633-
Resource Type:
Conference
Resource Relation:
Conference: Joint AIAA/SAE/ASME propulsion conference, Monterey, CA (United States), 28-30 Jun 1993
Country of Publication:
United States
Language:
English
Subject:
21 SPECIFIC NUCLEAR REACTORS AND ASSOCIATED PLANTS; PROPULSION REACTORS; DESIGN; RELIABILITY; PROPULSION SYSTEMS; COST ESTIMATION; ION PROPULSION; LUNA SPACE PROBES; MARS SPACE PROBES; PERFORMANCE; PLASMA DIAGNOSTICS; POWER AMPLIFIERS; TECHNOLOGY ASSESSMENT; AMPLIFIERS; ELECTRONIC EQUIPMENT; EQUIPMENT; PROPULSION; REACTORS; SPACE VEHICLES; VEHICLES; NESDPS Office of Nuclear Energy Space and Defense Power Systems; 210600* - Power Reactors, Auxiliary, Mobile Package, & Transportable

Citation Formats

Latham, T S, Roman, W C, and Johnson, B V. Plasma core nuclear rocket technology. United States: N. p., 1993. Web.
Latham, T S, Roman, W C, & Johnson, B V. Plasma core nuclear rocket technology. United States.
Latham, T S, Roman, W C, and Johnson, B V. 1993. "Plasma core nuclear rocket technology". United States.
@article{osti_5855415,
title = {Plasma core nuclear rocket technology},
author = {Latham, T S and Roman, W C and Johnson, B V},
abstractNote = {The nuclear lightbulb (NLB) rocket propulsion concept furnishes specific impulse above 2000 sec in conjunction with the greater-than-50,000 lb thrust levels required for rapid transit-time round-trip Mars missions requiring low initial mass in earth orbit. The NLB transfers energy from the gaseous nuclear fuel region to a hydrogen propellant via thermal radiation, thereby precluding material temperature constraints. An evaluation is presently made of technology and test method readiness for implementation and validation of this propulsion system concept. 13 refs.},
doi = {},
url = {https://www.osti.gov/biblio/5855415}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Jun 01 00:00:00 EDT 1993},
month = {Tue Jun 01 00:00:00 EDT 1993}
}

Conference:
Other availability
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