Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Cool Down Characteristics of 7 Tonf-class Liquid Rocket Engine for KSLV-II

한국형발사체 7톤급 액체로켓엔진 냉각 특성

  • Im, Ji-Hyuk (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Yu, Byungil (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Lee, Kwang-Jin (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Han, Yeoung-Min (Engine Test and Evaluation Team, Korea Aerospace Research Institute)
  • Received : 2020.09.18
  • Accepted : 2020.11.05
  • Published : 2021.02.28
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Abstract

Engine cool down process is necessary for the liquid rocket engines using cryogenic propellants in order to meet the requirement of engine inlet temperature. This paper evaluates the cool down characteristics of oxidizer supply pipeline and engine in prechill process prior to the engine firing tests, and calculate the quantity of liquid oxygen consumption.

한국형발사체에 사용되는 액체로켓엔진과 같이 극저온 추진제를 사용하는 엔진은 시험 전 시험설비 배관 및 엔진 냉각이 필수적으로 선행되어 엔진 입구 온도를 만족시켜야 한다. 본 논문에서는 한국형발사체 7톤급 액체로켓엔진의 시험 전 냉각 단계에서 소모되는 액체산소의 양을 확인하였고, 시험설비 배관 및 엔진 냉각특성을 평가하였다.

Keywords

References

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