액체로켓 엔진의 시동과정에 대한 1차원 해석

A one dimensional transient analysis was conducted on the startup process of a turbopump fed liquid rocket engine. A commercial code Flowmaster which has amassed reliability in flow system analyses such as the automobile and the airplane design was used. The required time was found to prime pipes, cooling channels of a combustion chamber, and the gas generator with propellant after the valves open. Also the optimal specification of a solid propellant starter of a turbine for stable and quick startup was designed. Furthermore the quantitative opening time of the shutoff valves was investigated in both oxidizer lines and fuel lines of combustion chamber and gas generator to avoid sharp temperature and pressure peak at the ignition. Concludingly the present study suggests a possibility to reduce the effort and risk to develop the startup process of a liquid rocket engine.