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A Study on Combustion Characteristics of Non-Circular Grain in Hybrid Rocket for RATO (Rocket-Assisted Take Off) System

RATO(Rocket-Assisted Take Off) 시스템 적용을 위한 하이브리드 로켓 비단공형 연료 그레인 기초 연소특성 연구

  • 김수진 (한국항공대학교 항공우주 및 기계공학부) ;
  • 고수한 (한국항공대학교 항공우주 및 기계공학과) ;
  • 김설희 (한국항공대학교 항공우주 및 기계공학과) ;
  • 김경모 (한국항공대학교 항공우주 및 기계공학부) ;
  • 이성근 (한국항공대학교 항공우주 및 기계공학부) ;
  • 한예찬 (한국항공대학교 항공우주 및 기계공학부) ;
  • 문희장 (한국항공대학교 항공우주 및 기계공학부)
  • Received : 2022.11.28
  • Accepted : 2022.12.26
  • Published : 2022.12.31

Abstract

In an attempt to apply hybrid rocket to the RATO (Rocket-Assisted Take Off) system, combustion characteristics of the non-circular grain were figured out in this study. Having larger combustion area, it was reconfirmed that the non-circular grain has advantages over regression rate, characteristic velocity and chamber pressure in which all gave higher values. Experiments were performed to understand the effect of the non-circular grain geometry over time where local regression rates depending on grain location were analyzed. It was found that the regression rate of five distinct locations were different. Partial conclusion driven was that these differences are due to the heat transfer caused by dissimilar distances from the flame layer. Besides, as combustion duration increased, the fuel port became circular, and the regression rate converged to a single value over the whole grain.

Keywords

Acknowledgement

본 논문은 정부(과학기술정보통신부)의 재원으로 한국연구재단-미래국방혁신기술개발사업(NRF-2020M3F6A1110342)의 지원을 받아 수행된 연구로 지원에 감사드립니다.

References

  1. Bettella, A., Moretto, F., Geremia, E., Bellomo, N., Petronio, D., and Pavarin, D., "Development of 20 kN hybrid rocket booster", 5th European Conference for Aeronautics and Space Sciences, Munich, Germany, 2013
  2. Takashi, T., Saburo, Y., and Kengo, Y., "Effects of swirling oxidizer flow on fuel regression rate of hybrid rockets", 35th Joint Propulsion Conference and Exhibit, 1999, p.2323.
  3. Hussain, M. M., Siddiqui, B., and Memon, A. "Design and analysis of rocket assisted takeoff high-speed UAV", 6th International Conference on Aerospace Science and Engineering, 2019.
  4. Yuasa, S., Shimada, O., Imamura, T., Tamura, T., and Yamamoto, T., "A technique for improving the performance of hybrid rocket engines", 35th IAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 1999, p. 2322.
  5. Larson, D. B., "Formulation and Characterization of praffin-based solid fuels containing novel additives for use in hybrid rocket motors", Master's Dissertation, Department of Mechanical and Nuclear Engineering, Pennsylvania University, Philadelphia, P.A., U.S.A., 2012.
  6. Vonderwell, D. J., Murray, I. F., and Heister, S. D., "Optimization of hybrid-rocket booster fuel-grain design", Journal of Spacecraft and Rockets, 32(6), 1995, pp.964-969. https://doi.org/10.2514/3.26716
  7. Kim, S., Kim, J., Moon, H., Sung, H., Lee, J., Kim, G., and Park, S., "Combustion characteristics of the cylindrical multi-port grain for hybrid rocket motor", 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009, p.5112.
  8. Kim, S., Lee, J., Moon, H., Kim, J., Sung, H., and Kwon, O. C., "Regression characteristics of the cylindrical multiport grain in hybrid rockets", Journal of Propulsion and Power, 29(3), 2013, pp.573-581. https://doi.org/10.2514/1.B34619
  9. Li, X., Tian, H., and Cai G., "Numerical analysis of fuel regression rate distribution characteristics in hybrid rocket motors with different fuel types", Science China Technological Sciences, 56(7), 2013, pp.1807-1817. https://doi.org/10.1007/s11431-013-5251-0
  10. Cai G., Zhang, Y., Wang, P., Hui, T., Zhao, S., and Yu, N., "Geometric effects of fuel regression rate in hybrid rocket motors", Science China Technological Sciences, 59(5), 2016, pp.807-813. https://doi.org/10.1007/s11431-016-6034-1
  11. Zhiliu Lu, "Comparison of cylindrical and non-cylindrical grain internal ballistic behavior of hybrid rocket engines and solid rocket motors", Master of Applied Science, Ryerson University, Toronto, Ontario, Canada, 2017.
  12. Cai, G., Zeng, P., Li, X., Tian, H., and Yu, N., "Scale effect of fuel regression rate in hybrid rocket motor", Aerospace Science and Technology, 24(1), 2013, pp.141-146. https://doi.org/10.1016/j.ast.2011.11.001
  13. Zhang, S., Hu, F., and Zhang, W., "Numerical investigation on the regression rate of hybrid rocket motor with star swirl fuel grain", Acta Astronautica, 127, 2016, pp.384-393.  https://doi.org/10.1016/j.actaastro.2016.06.017