한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제22권2호
  • /
  • Pages.115-124
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  • 2018
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  • 1226-6027(pISSN)
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  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
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초고속 비행체를 위한 준 자유흐름식 고공환경 모사시험설비의 설계 및 상온실험

Design and Cold Test of Semi-Freejet High Altitude Environment Simulation Test Facility for High-Speed Vehicle

  • Lee, Seongmin (School of Aerospace Engineering, Chungnam National University) ;
  • Yu, Isang (School of Aerospace Engineering, Chungnam National University) ;
  • Park, Jinsu (School of Aerospace Engineering, Chungnam National University) ;
  • Ko, Youngsung (School of Aerospace Engineering, Chungnam National University) ;
  • Kim, Sunjin (Fire Safety Engineering, Korea Chungnam State University) ;
  • Lee, Jungmin (Agency for Defense Development)
  • Received : 2017.07.18
  • Accepted : 2017.09.30
  • Published : 2018.04.01
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Abstract

본 연구에서는 초고속 비행체 고공환경 모사실험 설비에 대한 설계와 상온실험을 진행하였다. 시험 모델의 폐색율, 각도, 길이에 따른 변수실험을 진행하고, 변수에 따른 벽면압력변화를 확인하였다. 폐색율은 40%의 영역에서도 운용이 가능하며, 각도는 45도 이하의 크기에서 모델을 선정해야함을 확인하였다. 길이의 변수는 폐색율과 각도의 변수에 비하여 영향이 크지 않은 것을 확인하였다. 이를 통해서 초고속 비행체 시험설비에서 원뿔형 모델의 설계 변수에 따른 성능 데이터베이스를 확보하였다.

In this study, a cold flow test was carried out on a high-speed vehicle facility with a high-altitude environment simulator. Variable test was carried out according to the blockage ratio, angle, and length of the test model. It is confirmed that the blockage rate can be operated in the range of 40%, and that the model should be selected at an angle of 45 degrees or less. The variables of length are less dominant compared to the variables of blockage rate and angle. Through this, a database is obtained according to the parameters of the conical model of the high-speed vehicle test facility.

Keywords

References

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