Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Internal Flow Characteristics of Simulated Dual Pulse Rocket Motor by Using the Hot Gas and Cold Gas

Hot Gas와 Cold Gas를 이용한 모사 이중펄스 로켓 추진기관의 내부 유동 특성

  • Cho, Kihong (Department of Chemical Engineering, University of Seoul) ;
  • Park, Jungho (Department of Development, Hanwha Corporation Daejun Plant) ;
  • Kim, Euiyong (Department of Chemical Engineering, University of Seoul)
  • Received : 2014.12.23
  • Accepted : 2015.03.13
  • Published : 2015.04.01
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Abstract

Dual pulse rocket motor is a variant of solid rocket motor with two propellant grain separated by a pulse separation device. The major performance of such a rocket motor is influenced by the change in the hole area of pulse separation device to nozzle throat area ratio. In this study, we performed flow analysis to investigate the internal flow characteristics according to the pulse separation device hole area to nozzle throat area ratio change. Gases used flow analysis were used combustion gas of HTPB/AP composite propellant and nitrogen gas. Flow analysis results of the dual pulse rocket motor were validated by comparison with experimental results of pneumatics. Commercial CFD code ANSYS FLUENT 14.5 is used in this study to simulate flow analysis.

이중펄스 로켓 추진기관은 하나의 펄스분리장치에 의해 분리된 2개의 추진제 그레인을 가진 변형된 고체 추진기관이다. 이러한 추진기관의 주요 성능은 펄스분리장치 홀 면적대 노즐 목 면적비의 변화에 영향을 받는다. 본 연구에서는 펄스분리장치 홀 면적대 노즐 목 면적비 변화에 따른 내부유동특성을 고찰하기 위해 유동해석을 수행하였다. 유동해석에 사용된 기체로는 hot gas로 HTPB/AP계 복합추진제 연소가스와 cold gas로 질소가스롤 사용하였다. 이중펄스 로켓 추진기관의 내부유동해석 결과는 공압실험 결과와 비교 분석을 통해 검증하였다. 본 논문에서는 상용 CFD(Computational Fluid Dynamics) 코드인 ANSYS FLUENT V14.5를 이용하여 유동을 모사하였다.

Keywords

References

  1. Javed, A., Manna, P. and Chakraborty, D., "Numerical Simulation of a Dual Pulse Solid Rocket Motor Flow Field," Defence Science Journal, Vol. 62, No. 6, pp. 369-374, 2012. https://doi.org/10.14429/dsj.62.1418
  2. Sutton, G.P., Rocket Propulsion Elements, 7th ed., John Wiley & Sons Inc., New York, N.Y., U.S.A., pp. 419-577, 2001.
  3. Kong, J.A., Chun, P.A. and Thompson, A.M., "Multimission Propulsion Technology- Advanced Technology Demonstration(MMPTATD) Final Program Summary of Test Results and Conclusions," CPIA Pub. 630 (Vol. III), Oct. 1995.
  4. Naumann, K.W., Stadler, L.J., Trouillot, P., Weigand, A., Schilling, S. and Niedermaier, H., "Double Pulse Solid Rocket Motor Technology at Bayern-Chemie/Protac," 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Sacramento, CA, U.S.A., AIAA 2006-4761, July 2006.
  5. Wilcox, D.C., "A Half Century Historical Review of the k-w Model," 29th Aerospace Sciences Meeting and Exhibit, Reno, NV, U.S.A., AIAA 1991-615, Jan. 1991.
  6. Menter, F.R., "Two-Equation Eddy-Viscosity Turbulence Models for Engineering applications," AIAA Journal, Vol. 25, pp. 1473-1480, 1994.
  7. Raymond, M., Flow of Industrial Fluids: Theory and Equations, CRC Press, New York, N.Y., U.S.A., 2004.
  8. Cho, K.H., Park, J.H. and Kim, E.Y., "Analysis on the Internal Flow of the Hydraulic Dual Chambers Applying Various Orifice", Journal of the Korean Society of Propulsion Engineers, Vol. 18, No. 1, pp. 58-64, Feb. 2014. https://doi.org/10.6108/KSPE.2014.18.1.058