Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Study on Starting Pressure of Supersonic Exhaust Diffusers to Simulate high Altitude Environment

고고도 모사용 초음속 디퓨져의 시동압력에 대한 연구

  • 윤상규 (한국항공대학교 항공우주 및 기계공학부) ;
  • 염효원 (한국항공대학교 항공우주 및 기계공학부) ;
  • 김진곤 (한국항공대학교 항공우주 및 기계공학부) ;
  • 성홍계 (한국항공대학교 항공우주 및 기계공학부) ;
  • 김용욱 (한국항공우주연구원 추진기관 체계그룹) ;
  • 오승협 (한국항공우주연구원 추진기관 체계그룹)
  • Published : 2008.08.30
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Abstract

Theoretical and numerical approaches were conducted in order to study supersonic exhaust diffusers to simulate high altitude performance of rockets on the ground. A physical model of concern includes a rocket motor, vacuum chamber, and diffuser, which have axisymmetric configurations. An analysis was conducted to investigate operation characteristics of supersonic exhaust diffusers from a flow-development point of view. Emphasis was placed on theoretical formulation to predict the starting pressure of diffusers, the effect of the vacuum chamber size, and the minimum starting pressure of the rocket motor to start the diffuser.

고고도에서 작동하는 로켓의 작동 환경을 지상에서 모사하기 위한 초음속 디퓨져의 연구를 위하여 이론적 접근과 수치적 접근을 수행하였다. 물리적 모델은 축대칭 형상을 갖는 디퓨져, 진공챔버, 로켓모터로 구성하였으며, 유동 발달 측면에서 초음속 디퓨져 작동특성에 관한 연구를 수행하였다. 본 논문은 디퓨져의 시동압력 예측모델, 진공챔버 크기의 효과, 디퓨져 시동을 위한 로켓모터의 최소 시동압력에 대한 연구내용을 수록하였다

Keywords

References

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