The development of an injector/thruster concept capable of pulsing a liquid hydrogen/liquid oxygen attitude control propulsion system thruster over thrust and chamber-pressure ranges of 625 to 1250 lbF and 250 to 500 psia, respectively, is discussed. It is shown how continuing search for a simple light-weight, high-performance reaction control system concept led to successful operation tests at cryogenic propellant temperatures (150 and 45 degrees Rankine for oxygen and hydrogen, respectively). The analytical and experimental phases of the liquid/liquid thruster technology efforts are examined.
Demonstration of a pulsing liquid hydrogen/liquid oxygen thruster
Propulsion Conference ; 1973 ; Las Vegas, NV, US
01.11.1973
Aufsatz (Konferenz)
Keine Angabe
Englisch