한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제18권1호
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  • Pages.58-64
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  • 2014
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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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다양한 오리피스를 이용한 연결형 공압 챔버 내부 유동 해석

Analysis on the Internal Flow of the Hydraulic Dual Chambers Applying Various Orifice

  • Cho, Kihong (Department of Chemical Engineering, University of Seoul(Defense Agency for Technology and Quality)) ;
  • Park, Jungho (Department of Development, Hanwha Corporation DaeJun Plant) ;
  • Kim, Euiyong (Department of Chemical Engineering, University of Seoul)
  • 투고 : 2013.12.02
  • 심사 : 2014.01.13
  • 발행 : 2014.02.01
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⟨ 이전 논문 다음 논문 ⟩

초록

다양한 홀 크기를 갖는 오리피스를 이용하여 1, 2단 챔버를 구성하는 공압 모사모터를 제작하였다. 오리피스의 면적과 노즐 목 면적비에 따라 2단 챔버 작동 시 1단 챔버와 압력차가 발생한다. 이 압력차는 실제 추진기관 성능에 영향을 미치므로 오리피스 면적 및 설계에 대한 고찰이 필요하다. 2단 챔버 작동 시 1단 챔버 압력은 오리피스 크기 및 1단 챔버 형상에 따른 와류형성으로 에너지 손실이 발생한다. 본 논문에서는 상용 CFD(Computational Fluid Dynamics) 프로그램(ANSYS FLUENT V14.5)를 이용하여 유동을 모사하였다.

Hydraulic dual chamber, as the simulator for a dual pulse rocket motor, was tested by a high pressure device with various orifice-hole size being applied. Pressure difference occurs between 1st chamber and 2nd chamber depending on area ratio of the orifice to nozzle throat. Studying a design configuration of the orifice is essential to the motor development because pressure difference severely affects the rocket motor performance. It is noticed in this study that energy dissipation is caused by the vortex flow originating from the orifice as the 2nd chamber is operated. The flow field is simulated by a commercial computational fluid dynamics program, ANSYS FLUENT V14.5.

키워드

참고문헌

  1. Cho, W. M., Kim, W. H., Chang, H. R., Oh, J. Y., Lee, B. E., and Lee, J. W., "Study on Pulse Separation Device of Bulkhead Type for Solid Rocket Motors," Journal of the Korean Society of Propulsion Engineers, Spring Conference, 2009.
  2. Naumann, K. W., Stadler, L., Trouillot, P., Weigand, A., Zanelli, D., and Schilling, S., "Double pulse rocket motor technology at BAYERN CHEMIE PROTAC," 42nd AIAA/ ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, pp. 9-12, 2006.
  3. Kong, J. A., Chun, P. A., and Thompson, A. M., "Multimission Propulsion Technology- Advanced Technology Demonstration(MMPT -ATD) Final Program Summary of Test Results and Conclusions," CPIA Pub. 630 (Vol. III), Oct., 1995.
  4. Dallbello, T., Georgiadis, N. J., Yoder, D. A., and Keith, T. G., "Computational Study of Axisymmetric Off-Design Nozzle Flow," NASA TM-2003-212876, 2003.
  5. Wilcox, D. C., Turbulence Modeling for CFD, DCW Industries, Inc., La Canada, California, 1998.
  6. Raymond, M., Flow of Industrial Fluids: Theory and Equations, CRC Press, 2004.

피인용 문헌

  1. Internal Flow Characteristics of Simulated Dual Pulse Rocket Motor by Using the Hot Gas and Cold Gas vol.19, pp.2, 2015, https://doi.org/10.6108/KSPE.2015.19.2.001