Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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High Altitude Test Facility for Small Scale Liquid Rocket Engine

소형 액체로켓엔진 고공환경 모사시험 설비

  • Kim, Taewoan (School of Aerospace Engineering, Chungnam National University) ;
  • Kim, Wanchan (School of Aerospace Engineering, Chungnam National University) ;
  • Kim, Sunjin (School of Fire Safety Engineering, Chungnam State University) ;
  • Han, Yeoungmin (Propulsion Test and Evaluation Team, Korea Aerospace Research Institute) ;
  • Ko, Youngsung (School of Aerospace Engineering, Chungnam National University)
  • Received : 2014.12.23
  • Accepted : 2015.05.07
  • Published : 2015.06.01
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Abstract

A high altitude test facility which includes supersonic diffuser and ejector has been developed to simulate atmospheric pressure at 25 km using a 500 N class small scale liquid rocket engine. Also high altitude simulation test for the small scale liquid rocket engine was performed to verify the facility's performance. The experimental facility consists of high altitude simulation device, propellants supply system and coolant supply system. Low pressure condition corresponding to about 27 km(0.021 bar) altitude atmosphere was successfully simulated and a small scale liquid rocket engine thrust level was confirmed at the simulated condition by the high altitude test facility verification test.

본 연구에서는 소형 액체로켓엔진을 사용하여, 약 25 km(0.025 bar) 고도의 대기압 환경을 조성할 수 있는 초음속 디퓨저와 이젝터 조합의 고공시험 설비를 구축하였으며, 설비의 성능 검증 차원에서 소형 액체로켓엔진 고공환경 모사시험을 수행하였다. 시험 설비는 고공환경 모사장치와 추진제 공급설비 그리고 냉각수 공급설비로 구성된다. 본 고공시험 설비로 약 27 km(0.021 bar) 고도에 해당하는 대기 압력을 성공적으로 구현하였으며, 이때 소형 액체로켓엔진에서 발생하는 추력 성능을 확인하였다.

Keywords

References

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