NOZZLE SYSTEM DEVELOPMENT FOR HYBRID PROPULSION SYSTEM (U)

Development of a hybrid propulsion concept has created the requirement for a lightweight nozzle system capable of withstanding gas temperature in excess of 6200 F with condensible soilds in excess of 25% by weight for operation longer than 30 seconds. A series of nozzle material test firings illustr...

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Bibliographic Details
Main Authors: ROBINSON, A T, MCALEXANDER, R L, WYDRA, G J
Format: Report
Language:English
Subjects:
ABLATION
COOLING
COPPER
HIGH TEMPERATURE
HYBRID ROCKET ENGINES
IMPREGNATION
INTERMETALLIC COMPOUNDS
LIQUID METALS
Metallurgy and Metallography
PLASMA JETS
REFRACTORY MATERIALS
Rocket Engines
ROCKET NOZZLES
SHIELDING
SWEAT COOLING
Test Facilities, Equipment and Methods
TUNGSTEN
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Summary:Development of a hybrid propulsion concept has created the requirement for a lightweight nozzle system capable of withstanding gas temperature in excess of 6200 F with condensible soilds in excess of 25% by weight for operation longer than 30 seconds. A series of nozzle material test firings illustrated that tungsten impregnated with copper nozzle provided the best service. This led to the possibility that a transpiration effect or mass transfer cooling was being realized. A test program is now in process making use of pressure-driven liquid metal cooling through tungsten and graphite matrices subjected to a plasma-arc heat source. Tests indicate that liquid metal transpiration coolants, through a tungsten matrix coupled with nozzle inlet sacrificial materials, allow the possibility of longtime operation of a self-contained nozzle system suitable for hybrid or solid propellant rocket propulsion motors. (Author) Also available as Rept. no. GIDEP-563.55.00.00-X7-06.