Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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A Study on the Property of NEPE System Propellant with Respect to the Size of RDX

RDX 입도에 따른 NEPE계 추진제 특성 연구

  • Jang, Myungwook (Quality Assurance Team, Hanwha Corporation Daejeon Plant) ;
  • Kim, Taekyu (Quality Assurance Team, Hanwha Corporation Daejeon Plant) ;
  • Han, Haeji (Quality Assurance Team, Hanwha Corporation Daejeon Plant) ;
  • Yun, Jaeho (Quality Assurance Team, Hanwha Corporation Daejeon Plant) ;
  • Son, Hyunil (Quality Assurance Team, Hanwha Corporation Daejeon Plant)
  • Received : 2017.06.04
  • Accepted : 2017.10.15
  • Published : 2018.06.01
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Abstract

The propellant tile and crack which account for the greatest proportion of solid rockets are profoundly affected by viscosity and mechanical properties of solid propellant. In this paper solid propellant with nitrate ester polyester(NEPE) system has been researched for the viscosity, mechanical properties and burning properties with size and mixing ratio of RDX. the viscosity of propellant was changed significantly depending on the size of RDX and mixing ratio, and mechanical properties of NEPE system propellant were also varied. Considering both lower viscosity and stable mechanical properties, the optimum size and mixing ratio of RDX can be identified as the main factors to the NEPE system propellant.

고체 추진기관의 불량 발생 요인 중 가장 큰 부분을 차지하고 있는 추진제 기공 및 크랙은 추진제의 점도와 물성이 큰 영향을 미친다. 본 연구는 혼합형 고체 추진제의 한 종류인 나이트레이트 에스터 폴리이서(Nitrate Ester Polyester; NEPE)계열의 추진제에서 주로 사용되는 RDX의 입도 및 혼합 함량에 따른 추진제 점도, 기계적 물성 및 연소특성 변화를 관찰하였다. RDX 입도와 혼합 함량에 따라 미경화 추진제의 경시적 점도가 크게 변화가 되었으며, 이에 따른 추진제 물성 또한 변화가 있었다. 추진제의 낮은 점도와 안정된 기계적 물성을 동시에 고려할 때, RDX의 입도 및 혼합 함량은 NEPE계 추진제의 주요 인자로 확인할 수 있다.

Keywords

References

  1. Obeth, A.E., Principles of Solid Propellant Development, 1st ed. CPIA Publication, Baltimore, MD, USA, Ch 5, 1987.
  2. Sutton, G.P. and Biblarz, O., Rocket Propulsion Elements, 8th ed., John Wiley & Sons Inc., New York, N.Y., U.S.A., Ch 13, 2010.
  3. Yim, Y.J., "A Sturdy on the Burning Rate of Composite Solid Propellant," Ph. D. Thesis, Chemical Engineering, Yonsei University, Seoul, Korea, 1983.
  4. Jain, et al., "Influence of Ammonium Perchlorate on Properties of Composite Propellant," Defence Science Journal, Vol. 59, No. 3, pp. 294-299, 2009. https://doi.org/10.14429/dsj.59.1523
  5. Dorr, A., Sadiki, A. and Mehdizadeh, A., "A Discrete Model for the Apparent Viscosity of Polydisperse Suspensions Including Maximum Packing Fraction," Journal of Rheology, Vol. 57, No. 3, pp. 1-14, 2013. https://doi.org/10.1122/1.4754444
  6. Horine, C.L. and Madison, E.W., "Solid Propellant Processing Factors in Rocket Motor Design," NASA, Washington, D.C., U.S.A., SP-8057, 1971.