THE USE OF HYDROGEN IN NUCLEAR ROCKETS

Journal Article · Fri Sep 01 04:00:00 EDT 1961 · J. Brit. Interplanet. Soc.

OSTI ID:4801339

Wyatt, O H

A review is given of three papers by Wyatt, Newgard and Levoy, and Sams on the use of nuclear rockets with hydrogen propellent as single-stage Earth satellite launchers. They agree on the parameters and performances tabulated. The reactor core will be homogeneous uranium235/graphite in the form of cylinders between 3 and l2 ft in diameter, with voidage up to 0.5. With a 6-in. beryllium reflector, the minimum size may be determined by the maximum uranium concentration (here 1/sup 235/U:500 C) which does not reduce the mechanical strength, rather than the cost of the fuel investment. The maximum core temperature will be about 2500 deg C; the maximum propellent temperaand the power density around 200 Mw/ft./sup 3/ The payload for a 300-mile orbit will be up to 10 percentof the gross rocket mass, which for the above cores ranges from 10/sup 5/ to 7 x 10/sup 6/ lb, with thrusts about double these values. (auth)

• Research Organization: Hawker Siddeley Nuclear Power Co., London
• NSA Number: NSA-16-008436
• OSTI ID: 4801339
• Journal Information: J. Brit. Interplanet. Soc., Journal Name: J. Brit. Interplanet. Soc. Vol. Vol: 18
• Country of Publication: Country unknown/Code not available
• Language: English

Related Subjects

BERYLLIUM
CYLINDERS
ECONOMICS
GAS COOLANT
GRAPHITE
HIGH TEMPERATURE
HYDROGEN
JETS
MECHANICAL PROPERTIES
NESDPS Office of Nuclear Energy Space and Defense Power Systems
ORBITS
PAYLOAD
PERFORMANCE
POWER
PRESSURE
PROPULSION
QUANTITATIVE ANALYSIS
REACTOR CORE
REACTORS
REFLECTORS
ROCKETS
SPACE APPLICATIONS AND TECHNOLOGY
STANDARDS
TABLES
TEMPERATURE
URANIUM 235