PEBBLE BED NUCLEAR REACTORS FOR SPACE VEHICLE PROPULSION

Journal Article · Fri Apr 01 04:00:00 EST 1960 · Aero/Space Eng.

OSTI ID:4136771

Levoy, M M; Newgard, J J

The propulsion requirements necessary to launch a payload of 20 to 150,000 lbs in a 300 nautical mile orbit are discussed in conjunction with pebble- bed reactors. The design parameters are given for a typical space vehicle utilizing this type reactor. The reaotor core is a night cylinder composed of graphite spheres impregnated with uranium. The reflector thickness is six inches of random sized BeO pellets. The hydrogen propellant enters the core and reflector at -367 deg F and 400 psia; exits from the core at 4,200 deg F and 100 psia; and leaves the reflector at 1,500 deg F and 150 psia. Schematics are given for the rocket with the reactor, and for the reactor. Graphical representations of reactor and core parameters are included. (B.O.G.)

• Research Organization: Thiokol Chemical Corp., Denville, N.J.
• NSA Number: NSA-14-016472
• OSTI ID: 4136771
• Journal Information: Aero/Space Eng., Journal Name: Aero/Space Eng. Vol. Vol: 19, No. 4
• Country of Publication: Country unknown/Code not available
• Language: English

Related Subjects

BERYLLIUM OXIDES
CONFIGURATION
DIAGRAMS
GRAPHITE MODERATOR
HIGH TEMPERATURE
HYDROGEN
IMPREGNATION
LOW TEMPERATURE
PBR
PEBBLE BED
PELLETS
PLANNING
PROPULSION
REACTOR CORE
REACTOR TECHNOLOGY
REACTORS
REFLECTORS
ROCKETS
SPACE VEHICLES
SPHERES
THICKNESS
USES