Monopropellant Hydrazine Engine Evaluation with Shell 405 and Shell X-4 Catalysts.
Final rept. Nov 70-Aug 71,
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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Test and evaluation of five 75-lb thrust monopropellant hydrazine engines developed by Rocket Research Corporation were performed with both Shell 405 and Shell X-4 catalysts to determine the suitability of the hardware for meeting initial Post Boost Propulsion System PBPS design requirements. The original engines with Shell 405 catalyst failed to deliver the required minimum thrust level 71.25 lbf when tested at the AFRPL. Two of the test engines were refurbished with Shell X-4 catalyst and exceeded all of the minimum specified design and operating requirements with a delivered vacuum thrust and specific impulse in excess of 75 lbf and 220 seconds, respectively, for the complete design life of 500 seconds. A third refurbished test engine was subjected to two ambient restarts and failed to deliver the minimum required thrust and specific impulse after 280 seconds of operation. Author
- Liquid Propellant Rocket Engines
- Liquid Rocket Propellants