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Title: SELECTION OF POWER REQUIREMENTS FOR NUCLEAR-ELECTRIC SPACECRAFT MISSIONS

Abstract

A method is presented for bracketing propulsion power requirements for spacecraft missioms consistent with specific launch vehicle boost constraints and anticipated stateof-the-art reactor-conversion system development. A Mars orbiter mission is taken as an illustrative example of the basic approach. Having selected launch vehicle, payload, and flight time, the distribution of powerplant and propellant weight is discussed. Curves are presented which indicate the minimum power requirement for the mission, the power range which affords maximum powerplant design flexibility, and the powerplant specific weights which must be attained to accomplish the mission. The interplay between mission requirements and powerplant development is indicated. An indication is given that a nuclear electric plant in the power range of 100 kw(e) propulsion at a specific weight in the range of 35 lb/kw(e) can accomplish a useful Mars orbiter mission in a reasonable flight time and delivering a useful scientific payload. Data are presented for two Jupiter missions. (auth)

Authors:
Publication Date:
Research Org.:
California Inst. of Tech., Pasadena. Jet Propulsion Lab.
OSTI Identifier:
4035994
Report Number(s):
JPL-TR-32-114
NSA Number:
NSA-15-023163
DOE Contract Number:  
NASW-6
Resource Type:
Technical Report
Resource Relation:
Other Information: Orig. Receipt Date: 31-DEC-61
Country of Publication:
United States
Language:
English
Subject:
GENERAL AND MISCELLANEOUS; ELECTRICITY; JUPITER; MARS PLANET; ORBITS; PAYLOAD; PLANETS; PROPULSION; REACTORS; SPACE FLIGHT; SPACE VEHICLES

Citation Formats

Davis, J P. SELECTION OF POWER REQUIREMENTS FOR NUCLEAR-ELECTRIC SPACECRAFT MISSIONS. United States: N. p., 1961. Web.
Davis, J P. SELECTION OF POWER REQUIREMENTS FOR NUCLEAR-ELECTRIC SPACECRAFT MISSIONS. United States.
Davis, J P. Wed . "SELECTION OF POWER REQUIREMENTS FOR NUCLEAR-ELECTRIC SPACECRAFT MISSIONS". United States.
@article{osti_4035994,
title = {SELECTION OF POWER REQUIREMENTS FOR NUCLEAR-ELECTRIC SPACECRAFT MISSIONS},
author = {Davis, J P},
abstractNote = {A method is presented for bracketing propulsion power requirements for spacecraft missioms consistent with specific launch vehicle boost constraints and anticipated stateof-the-art reactor-conversion system development. A Mars orbiter mission is taken as an illustrative example of the basic approach. Having selected launch vehicle, payload, and flight time, the distribution of powerplant and propellant weight is discussed. Curves are presented which indicate the minimum power requirement for the mission, the power range which affords maximum powerplant design flexibility, and the powerplant specific weights which must be attained to accomplish the mission. The interplay between mission requirements and powerplant development is indicated. An indication is given that a nuclear electric plant in the power range of 100 kw(e) propulsion at a specific weight in the range of 35 lb/kw(e) can accomplish a useful Mars orbiter mission in a reasonable flight time and delivering a useful scientific payload. Data are presented for two Jupiter missions. (auth)},
doi = {},
url = {https://www.osti.gov/biblio/4035994}, journal = {},
number = ,
volume = ,
place = {United States},
year = {1961},
month = {5}
}

Technical Report:
Other availability
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