Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Development Trend of Korean Staged Combustion Cycle Rocket Engine

한국형 다단연소사이클 로켓엔진 개발 동향

  • Kim, Chae-hyoung (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Han, Yeoung Min (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Cho, Namkyung (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Kim, Seung-Han (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) ;
  • So, Younseok (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Woo, Seongphil (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Im, Ji-Hyuk (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Hwang, Chang Hwan (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Lee, Jungho (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Kim, Jin-han (Rocket Engine Development Office, Korea Aerospace Research Institute)
  • Received : 2017.06.03
  • Accepted : 2017.09.10
  • Published : 2018.06.01
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Abstract

Korea Aerospace Research Institute has developed a staged combustion cycle rocket (SCCR) engine with high specific impulse to send a 3-ton class satellite into geostationary orbit while conducting a Korean Space Launch Vehicle (KSLV) II project. The SCCR engine is different from the KSLV-II engine, which is an open cycle engine using a gas-generator. The SCCR engine with a closed cycle engine is composed of a pre-burner, a turbo pump, and a main combustor. The technology demonstration model (TDM0) was assembled and tested in the 7ton-class engine combustion test facility of Naro Space Center, and the combustion test was successfully conducted.

한국형발사체(KSLV-II) 개발과 함께 지구정지궤도 발사를 위해 비추력이 높은 다단연소사이클 로켓 엔진 개발이 한국항공우주연구원에서 진행되고 있다. 다단연소사이클 로켓엔진은 한국형발사체 엔진과 달리 가스발생기를 사용하는 개방형 엔진이 아니며, 크게 예연소기, 터보펌프, 주연소기로 구성되어 있는 폐쇄형 엔진이다. 기술검증시제 개발용 모델(TDM0)을 조립하여 나로우주센터의 7톤급 엔진 연소시험설비에서 연소시험이 진행되고 있으며, 기술검증시제 모델의 연소시험은 성공적으로 수행되었다.

Keywords

References

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