Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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CFD Simulation of Combustion and Extinguishment of Solid Propellants by Fast Depressurization

고체 추진제의 연소 및 빠른 감압에 의한 소화 모델 CFD 모사

  • Lee, Gunhee (Department of Chemical Engineering, Hanbat National University) ;
  • Jeon, Rakyoung (Department of Chemical Engineering, Hanbat National University) ;
  • Jung, Minyoung (Department of Chemical Engineering, Hanbat National University) ;
  • Shim, Hongmin (Agency for Defense Development) ;
  • Oh, Min (Department of Chemical Engineering, Hanbat National University)
  • Received : 2018.08.24
  • Accepted : 2018.11.29
  • Published : 2019.02.01
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Abstract

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 MPa to a final pressure of 2.5 MPa at a depressurization rate of approximately -912 MPa/s.

본 연구는 고체추진기관의 추력제어와 불필요한 연소방지를 위해 연소 중 빠른 감압을 통한 소화모델의 3차원 로켓 유동해석을 수행하였다. 핀틀을 적용하여 감압속도에 따른 연소실 유동변화와 소화과정에 대한 전산유체역학 모사를 수행하였다. 암모니움퍼클로라이트 단일 산화제를 사용하였으며, 연소 중 가스상의 온도, 압력, 연소율 등의 주요 변수의 동적 거동을 예측하였다. 초기압력 7 MPa에서 감압 후 최종 압력 2.5 MPa로 약 -912 MPa/s로 감압 시, 연소실의 동적 거동을 확인하였다.

Keywords

Acknowledgement

Supported by : 국방과학연구소

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