Transtage Monopropellant Attitude Control Engine Evaluation.
Final rept. Apr 68-Sep 69,
AIR FORCE ROCKET PROPULSION LAB EDWARDS AFB CA
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A program was conducted to evaluate the performance of the Transtage attitude control engine. Three injector inlet pressures 185 psia, 275 psia, and 370 psia were used to simulate both the extremes in inlet pressure and the mean inlet pressure encountered in blowdown operation of the engine. All tests were performed at simulated altitude, and high altitude ignition delay tests were performed at altitudes in excess of 370,000 feet. The measured parameters were pressure integral, response time, decay time, fuel consumption, ignition delay and chamber pressure roughness. Those parameters were plotted against chamber temperature and the results indicate that the efficiency of the engine increases with increased chamber temperature. Thermal equilibrium plots for the injector and the feed tube were also developed, as was a plot of engine throat area versus temperature. The program resulted in an accumulated engine run time of 803 seconds with a total of 6530 engine firings. Author
- Combustion and Ignition
- Liquid Propellant Rocket Engines
- Ground Support Systems and Facilities for Space Vehicles