Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Investigation on Chilling Procedure for LOX Supply System for Liquid Rocket Engine

액체로켓엔진 산화제 공급부 냉각과정 고찰

  • Cho, Nam-Kyung (Engine Test & Evaluation Team, Korea Aerospace Research Institute) ;
  • Seo, Dae-Bahn (Engine Test & Evaluation Team, Korea Aerospace Research Institute) ;
  • Yoo, Byung-Il (Engine Test & Evaluation Team, Korea Aerospace Research Institute) ;
  • Kim, Seong-Han (Engine Test & Evaluation Team, Korea Aerospace Research Institute) ;
  • Han, Yeoung-Min (Engine Test & Evaluation Team, Korea Aerospace Research Institute)
  • Received : 2018.08.07
  • Accepted : 2019.05.10
  • Published : 2019.06.01
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Abstract

For rockets using cryogenic liquid hydrogen or liquid oxygen, chilling is required to avoid cavitation and surge problems. Chilling is categorized by the initial chilling/filling stage and the low-temperature maintenance stage. In addition, to improve satellite insertion capability, a multi-ignition capability is required and accordingly chilling to prepare for the next ignition during low-gravity coasting is also required. This paper describes the overall aspects of filling and low temperature maintain marinating for the booster and the upper stage engine including chilling for multi-ignition.

극저온 액체산소나 액체수소를 사용하는 액체로켓 엔진은 냉각이 충분하지 않을 경우 펌프 인입부에서 의 케비테이션과 연소기 메니폴드부에서의 급격한 기화에 의한 서지 현상이 발생할 수 있다. 극저온 추진제 사용을 위한 냉각은 유로의 충전을 위한 냉각/충전단계와 충전 후 온도유지 단계로 구분된다. 발사체의 위성투입 능력 향상을 위해서는 상단엔진의 다점화 기능이 필요하며 다점화를 위해서는 무추력 구간 중 다음 시동을 위한 냉각이 수행되어야 한다. 본 연구에서는 지상에서의 엔진의 냉각/충전 및 온도유지, 그리고 상단 엔진이 1차 점화하기 위한 냉각과 무추력 구간에서의 냉각유지, 그리고 다점화를 위한 냉각에 대해 논의한다.

Keywords

References

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