Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)
- Volume 5 Issue 1
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- Pages.18-25
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- 2001
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- 1226-6027(pISSN)
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- 2288-4548(eISSN)
Performance Analysis of Secondary Gas Injection for a Conical Rocket Nozzle TVC(II)
2차 가스분사에 의한 원추형 로켓노즐 추력벡터제어 성능해석 (II)
- Song, Bong-Ha (Yonsei University, Dept. of Mechanical Engineering) ;
- Ko, Hyun (Yonsei University, Dept. of Mechanical Engineering) ;
- Yoon, Woong-Sup (Yonsei University, Dept. of Mechanical Engineering) ;
- Lee, Sang-Kil (Advanced Institute of Military Science and Technology)
- Published : 2001.03.01
Abstract
The results of systematic numerical experiments of secondary gas injection thrust vector control are presented. The effects of secondary injection system such as injection location and nozzle divergent cone angle onto the overall performance parameters such as thrust ratio, specific impulse ratio and axial thrust augmentation, are investigated. Complex nozzle exhaust flows induced by the secondary jet penetration is numerically analyzed by solving unsteady three-dimensional Reynolds-averaged Navier-Stokes equations with Baldwin-Lomax turbulence model for closure. Numerical simulations compared with the experiments of secondary air injection into the rocket nozzle of
2차 가스 분사 추력벡터 제어 성능 해석을 위한 체계적인 수치계산을 수행하였다. 분사위치와, 노즐 팽창각이 압력비, 추력비, 비추력비 및 축추력 증대와 같은 전체 성능 파라미터에 미치는 2차 분사의 효과를 고찰하였다. 2차 제트 분사에 의한 복잡한 노즐 배기 유동에 대한 수치 해석은 Baldwin-Lomax 난류 모델을 포함하는 비정상 3차원 레이놀즈 평균 Navier-Stokes 방정식을 이용하여 수행하였고, 팽창 팽착반각이
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