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Investigation of axial-injection end-burning hybrid rocket motor regression

  • 투고 : 2016.03.31
  • 심사 : 2016.09.13
  • 발행 : 2017.05.25

초록

The axial-injection end-burning hybrid rocket proposed twenty years ago by the authors recently recaptured the attention of researchers for its virtues such as no ${\zeta}$ (oxidizer to fuel mass ratio) shift during firing and good throttling characteristics. This paper is the first report verifying these virtues using a laboratory scale motor. There are several requirements for realizing this type of hybrid rocket: 1) high fuel filling rate for obtaining an optimal ${\zeta}$; 2) small port intervals for increasing port merging rate; 3) ports arrayed across the entire fuel section. Because these requirements could not be satisfied by common manufacturing methods, no previous researchers have conducted experiments with this kind of hybrid rocket. Recent advances in high accuracy 3D printing now allow for fuel to be produced that meets these three requirements. The fuel grains used in this study were produced by a high precision light polymerized 3D printer. Each grain consisted of an array of 0.3 mm diameter ports for a fuel filling rate of 98% .The authors conducted several firing tests with various oxidizer mass flow rates and chamber pressures, and analysed the results, including ${\zeta}$ history, using a new reconstruction technique. The results show that ${\zeta}$ remains almost constant throughout tests of varying oxidizer mass flow rates, and that regression rate in the axial direction is a nearly linear function of chamber pressure with a pressure exponent of 0.996.

키워드

과제정보

연구 과제 주관 기관 : Ministry of Education, Science, Sports and Culture

참고문헌

  1. Barato, F., Grosse, M. and Bettella, A. (2014), "Hybrid rocket fuel residuals-an overlooked topic", Proceedings of the 50th AIAA/SAE/ASEE Joint Propulsion Conference, Cleveland, USA, July.
  2. Chiaverini, M.J. and Kuo, K.K. (2007), Fundamentals of Hybrid Rocket Combustion and Propulsion, American Institute of Aeronautics and Astronautics, Reston, USA.
  3. Frederick, R.A. and Greiner, B.E. (1996), "Laboratory-scale hybrid rocket motor uncertainty analysis", J. Propuls. Pow., 12(3), 605-611. https://doi.org/10.2514/3.24076
  4. Gordon, S. and McBride, B.J. (1994), "Computer program for calculation of complex chemical eEquilibrium", NASA Reference Publication, RP-1311.
  5. Hashimoto, N. (2004), "End-burning type hybrid rocket", Ph.D. Dissertation, Hokkaido University, Sapporo, Japan.
  6. Hashimoto, N., Kato, T., Nagata, H., Akiba, R. and Kudo, I. (2001), "A preliminary study of end-burning hybrid rocket, Part 2: Combustion characteristics", J. JPN Soc. Aeronaut. Space Sci., 49(565), 40-47.
  7. Hashimoto, N., Nagata, H., Totani, T. and Kudo, I. (2006), "Determining factor for the blowoff limit of a flame spreading in an opposed turbulent flow in a narrow solid-fuel duct", Combus. Flame, 147(3), 222-232. https://doi.org/10.1016/j.combustflame.2006.07.015
  8. Hitt, M.A. and Frederick, R.A. (2015), "Testing and modeling of a porous polyethylene axial-injection endburning hybrid rocket motor", Proceedings of the 51st AIAA/SAE/ASEE Joint Propulsion Conference, Orlando, USA, July.
  9. Kato, T., Hashimoto, N., Nagata, H., Akiba, R. and Kudo, I. (2001), "A preliminary study of end-burning hybrid rocket, Part 1: Combustion stability", J. JPN Soc. Aeronaut. Space Sci., 49(565), 33-39.
  10. Li, X.T., Tian, H., Yu, N. and Cai, G.B. (2015), "Experimental investigation of combustion in axialinjection end-burning hybrid rocket motor", J. Propuls. Pow., 31(3), 930-936. https://doi.org/10.2514/1.B35480
  11. Nagata, H., Nakayama, H., Watanabe, M., Wakita, M. and Totani, T. (2014), "Accuracy and applicable range of a reconstruction technique for hybrid rockets", Adv. Aircraft Spacecraft Sci., 1(3), 273-289. https://doi.org/10.12989/aas.2014.1.3.273
  12. Nagata, H., Okada, K., Sanda, T., Kato, T., Akiba, R., Satori, S. and Kudo, I. (1997), "Combustion characteristics of fibrous fuels for dry towel hybrid rocket motor", J. Space Technol. Sci., 13(1), 11-16.
  13. Nagata, H., Teraki, H., Saito, Y., Kanai, R., Yasukochi, H., Wakita, M. and Totani, T. (2015), "Verification firings of end-burning type hybrid rockets", Proceedings of the 51st AIAA/SAE/ASEE Joint Propulsion Conference, Orlando, USA, July.

피인용 문헌

  1. Investigation of Throttling Response Characteristics of Axial-Injection End-Burning Hybrid Rockets vol.16, pp.1, 2018, https://doi.org/10.2322/tastj.16.9