BOUNDARY CONDITIONS FOR NUCLEAR PROPULSION
Rocket-vehicle performance is analyzed and relations between nuclear- rocket motor, propellant pumping plant, propellant, propellant tank structure, and deadload defined to include all remaining equipment, are graphically expressed. Performance curves are given for hydrogen (propellant density = 4.4 1b/ft/sup 3/) and ammonia (propellant density = 44 lb/ft/sup 3/) in terms of propellant performance and peak operating temperature up to 50,000 deg R for an isentropic nozzle expansion efficiency of 80 per cent. Nuclear propulsion performance curves are given in terms of reactor-fuel loss and propellant specific impulse vs. vehicle characteristic velocity. A design is given for a regeneratively-cooled nuclear and electric propulsion system. Free-fall flight must involve accelerations of the order of 10/sup -4/ to 10/sup -3/ gr. Nuclear- rocket-motor specific power output should be aimed ior the range 0.5 < K/sub r/ < 1.5 Mw/lb for ground-launched nuclear-rocket vehicles. Propellant specific impulse should be in the range 1000 < I/sub sp/ < 2500 sec for NH/sub 3/ and 2000 < I/sub sp/<5000 sec for H/sub 2/ for a useful payload capacity. Gaseous reactors should be able to operate at peak temperatures of 20,000 < T/sub c/ < 60,000 deg R. (C.J.G.)
- Research Organization:
- Los Alamos Scientific Lab., N.Mex.
- NSA Number:
- NSA-14-003264
- OSTI ID:
- 4225172
- Journal Information:
- Astronautics, Journal Name: Astronautics Vol. Vol: 4, No. 10
- Country of Publication:
- Country unknown/Code not available
- Language:
- English
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