Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Pressure Control of Staged Combustion Liquid Rocket Engine

다단연소사이클 액체 로켓엔진의 압력제어에 대한 연구

  • Hwang, Changhwan (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Lee, Kwangjin (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) ;
  • Jeon, Junsu (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Lee, Jungho (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Yoo, Byungil (Engine Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Han, Yeoungmin (Engine Test and Evaluation Team, Korea Aerospace Research Institute)
  • Received : 2017.06.03
  • Accepted : 2017.11.14
  • Published : 2018.08.01
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Abstract

For the control of pre-burner combustion pressure, the open angle of the TTR (Throttle for Thrust Regulation) valve was varied from $143^{\circ}$ to $185^{\circ}$ while testing cold flow, ignition, and combustion. The major performance variables of rocket engines and hydraulic performance of the TTR valve regarding the open angle were verified. However, the controllability of pre-burner combustion pressure was not verified due to the limitations of the test. Comprehensive research will be done after addressing these problems.

나로우주센터에 구축/개발된 3단 엔진 연소시험설비에서 다단연소사이클 액체 로켓엔진의 시험을 수행하였다. 수류시험과 점화시험, 연소시험이 이루어졌으며 예연소기의 연소압력 제어를 위한 TTR의 개도를 $143^{\circ}$에서 $185^{\circ}$까지 변화시키며 시험을 수행하였다. 시험 결과 엔진의 주요성능과 TTR 개도에 의한 수력학적 변화를 확인하였지만 연소압력의 제어성 확인을 위한 결과는 얻지 못하였다. 향후 본 논문의 연구에서 도출된 개선점을 보완한 예연소기 압력제어 연구가 이루어질 것이다.

Keywords

References

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