한국전산유체공학회:학술대회논문집
- 한국전산유체공학회 2008년도 춘계학술대회논문집
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- Pages.324-327
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- 2008
액체로켓엔진의 2단 시동에 관한 연구
A Study on the 2-Stage Startup of Liquid Rocket Engine
초록
Two stage startup of high thrust liquid rocket engine can reduce the abrupt impulse to the vehicle and engine by changing oxidizer flow rate to the combustion chamber. Also it ensures stable ignition of combustion chamber against hard start and to prevent pump stall by the sudden supply of large mass flow rate. However high discharge pressure of oxidizer pump or temperature rise in gas generator may be a problem in applying the preliminary stage. To solve this problem, we analyzed the effect of the slope of oxidizer pump's head curve and the oxidizer mass flow rate to combustion chamber during preliminary stage using the rocket engine startup analysis code. A moderate slope(
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