Development of High Response 75-lbf Monopropellant Rocket Engine Assemblies.
Final rept. 24 Apr 68-4 Mar 69,
ROCKET RESEARCH CORP REDMOND WASH
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A development program on a 75-lbf monopropellant hydrazine rocket engine assembly REA for advanced postboost propulsion applications was carried out for the Air Force Rocket Propulsion Laboratory. Design verification tests were conducted with reactors at two different bed loadings to establish reactor parameters capable of meeting performance, response, and life requirements. Firings were conducted with a standard duty cycle consisting of both steady-state and pulse-mode operation. The duty cycle was repeated as required to demonstrate nominal life and life margin capability. The injector thermal design was verified by successful operation at maximum injector head temperature. The integrity of the catalyst bed was demonstrated by life margin firings conducted following random vibration and shock tests. Altitude firing tests demonstrated steady-state performance, response, and tail-off parameters. Outer skin temperature measurements revealed a local hot spot in excess of specification requirements. This problem was resolved by redesign of the heat shield. Five end-item REAs and three spare propellant valves were delivered to AFRPL where they will be subjected to environmental and firing tests to investigate unit-to-unit performance and repeatability. Author
- Liquid Propellant Rocket Engines