Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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A Study on Characteristic of Extinguishment for Solid Propellants Composition by Rapid Depressurization

압력 강하에 따른 추진제 조성별 소화 특성 분석

  • Received : 2017.01.24
  • Accepted : 2017.05.22
  • Published : 2017.10.01
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Abstract

Extinguishment of a burning solid propellant is difficult, however, dynamic extinction can be induced by fast depressurization in combustion chamber. This paper describes experimental results for the characteristics of extinguishment for composite solid propellants by rapid depressurization. For various composition of solid propellants, depressurization ratio which can induce extinguishment of combustion was obtained using experimental apparatus with rupture disk. Experimental results showed that particle size of oxidizer, mixing ratio of oxidizers with different particle size and contents of metal fuel can affect on the characteristics extinguishement for solid propellant.

연소 중인 고체추진제는 일반적으로 소화가 어렵지만, 연소실 내의 압력을 급격하게 강하시키면 추진제는 동적소화가 일어난다. 본 연구에서는 복합형 고체 추진제의 조성별 소화특성에 따른 실험적 연구에 대해 기술하였다. 폐쇄형 연소 챔버에 노즐 및 파열판을 장착하여 압력 강하시점, 압력 강하율, 초기 압력을 조절할 수 있는 실험장치를 구성하였다. 이 장치를 이용하여 추진제 조성별로 소화가 가능한 임계 압력 강하율을 실험적으로 연구하였다. 실험 결과 산화제의 입자크기, 산화제 혼합비, 알루미늄 첨가 유무가 고체 추진제의 소화 특성에 큰 영향을 주는 것으로 나타났다.

Keywords

References

  1. Hodge, K., Crofoot, T. and Nelson, S., "Gelled propellants for tactical missile applications," 35th Joint Propulsion Conference and Exhibit, Los Angeles, C.A., U.S.A., AIAA 1999-2976, Jun. 1990.
  2. Stadler, L., Hoffmann, S., Huber, J., Naumann, K. and Stingl, R., "The flight demonstration of the double pulse motor demonstrator MSA," 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, Nashvile, T.N., U.S.A., AIAA 2010-6756, Jul. 2010.
  3. Mongia, H.C. and Ambs, L.L., "A Model for the combustion and extinction of composite solid propellants during depressurization," Combustion and Flame, Vol. 22, No. 1, pp. 59-69, 1974. https://doi.org/10.1016/0010-2180(74)90010-8
  4. T'ien, J.S., "Theoretical criterion for dynamic extinction of solid propellants by fast depressurization," Combustion science and technology, Vol. 9, Issue 1-2, pp. 37-39, 1974. https://doi.org/10.1080/00102207408960334
  5. Donde, R., Riva, G. and Luca, L.D., "Experimental and theoretical extinction of solid rocket propellants by fast depressurization," Acta Astronautica, Vol. 11, No. 9, pp. 569-576, 1984. https://doi.org/10.1016/0094-5765(84)90029-8
  6. Hwang, Y.S., "Experimental Study on the Extinction Characteristics of the Solid Propellant," Journal of the Korean Society of Propulsion Engineers, Vol. 8, No. 3, pp. 61-67, 2004.
  7. Jeong, H.G. and Lee, C.J., "Dynamic Extinction of Solid Propellants by Depressurization of Combustion Chamber," Journal of the Korean Society for Aeronautical & Space Sciences, Vol. 30, No. 2, pp. 91-97, 2002. https://doi.org/10.5139/JKSAS.2002.30.2.091
  8. Carl, C.C., "Effect of Composition on Combustion of Solid Propellants during a Rapid Pressure Decrease," NASA TM-D1559, 1962.