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고체 추진제의 연소 및 빠른 감압에 의한 소화 모델 CFD 모사
이건희(Gunhee Lee),전락영(Rakyoung Jeon),정민영(Minyoung Jung),심홍민(Hongmin Shim),오민(Min Oh) 한국추진공학회 2019 한국추진공학회지 Vol.23 No.1
In this study, an extinguishment model of a three-dimensional solid propellant rocket was developed by combustion and fast depressurization to control the thrust of a solid rocket. Computational fluid dynamics simulation was carried out to ascertain the change in flow patterns in the combustion chamber and the extinguishment process by using a pintle. An ammonium perchloride was used as the target propellant and the dynamic behavior of its major parameters such as temperature, pressure, and burning rate was predicted using the combustion model. The dynamic behavior of the combustion chamber was confirmed by fast depressurization from an initial pressure of 7 ㎫ to a final pressure of 2.5 ㎫ at a depressurization rate of approximately -912 ㎫/s.