Effect of HMX Content on Agglomeration and Condensed Phase Combustion Products of AP/HMX/Al/HTPB Propellants

被引：0
|
作者：
Gou D.-L. [1 ]
Ao W. [1 ]
Liu L. [1 ]
Wu H.-M. [2 ]
Liu P.-J. [1 ]
He G.-Q. [1 ]
机构：
[1] Science and Technology on Combustion, Internal Flow and Thermo‑Structure Laboratory, Northwestern Polytechnical University, Xi'an
[2] The 41st Institute of the Fourth Academy of CASC, Xi'an
来源：
Hanneng Cailiao/Chinese Journal of Energetic Materials | 2022年 / 30卷 / 06期
关键词：
Agglomeration; Combustion; Condensed combustion products; Ignition; Octogen(HMX); Solid propellant;
D O I：
10.11943/CJEM2021183
中图分类号：
学科分类号：
摘要：
As an energetic material, octogen(HMX) is widely used in solid propellants. While improving the energy performance of the propellant, it also changes the combustion process of the propellant. To study the effect of HMX content on the ignition, combustion, and agglomeration properties of propellant and its condensed phase combustion products (CCPs), burning surface photography, laser ignition and collection of the CCPs were used for testing and studying typical AP/HTPB/Al/HMX propellants with HMX contents ranging 0%-10%. Results show that as the HMX content increases from 0 to 10%, the ignition delay time increases from 191 ms to 286 ms, and both the burning rate and pressure exponent of the propellent decreases. The volume average particle size of the CCPs increased from 48.1 μm to 138.3 μm. The propellent with 10% HMX has the highest agglomeration degree on the burning surface, while the propellent with 8% HMX has the highest active aluminum content in the CCPs. © 2022, Editorial Board of Chinese Journal of Energetic Materials. All right reserved.
引用
收藏
页码：571 / 578
页数：7
相关论文
共 30 条
  • [1] MA Xiu-fang, ZHAO Feng, XIAO Ji-Jun, Et al., Simulation study on structure and property of HMX‑based multi‑components PBX, Explosion and Shock Waves, 27, 2, pp. 109-115, (2007)
  • [2] NAYA T, KOHGA M., Influences of particle size and content of HMX on burning characteristics of HMX-based propellant, Aerospace Science & Technology, 27, 1, pp. 209-215, (2013)
  • [3] GAO H, HOU X T, KE X, Et al., Effects of nano‑HMX on the properties of RDX‑CMDB propellant: Higher energy and lower sensitivity, Defence Technology, 13, 5, pp. 323-326, (2017)
  • [4] XU Ya-bei, TAN Ying-xin, CAO Wei-guo, Et al., Thermo‑deco‑ mposition performance of RDX and the effect of HMX on its thermo‑stability, Chinese Journal of Energetic Materials (Hanneng Cailiao), 28, 2, pp. 157-163, (2020)
  • [5] JIA Xiao-feng, LI Bao-xuan, WANG Shi-ying, Effect of particle size of HMX/RDX on combustion characteristics of nitramine propellants under high and low pressure, Journal of Solid Rocket Technology, 33, 3, pp. 319-322, (2010)
  • [6] MA Feng-guo, JI Shu-tian, WU Wen-hui, Et al., Lowering the pressure exponents of NEPE propellant by coated HMX and burning rate catalysts, Chinese Journal of Energy Materials, 7, 4, pp. 166-168, (1999)
  • [7] KIM E S, YANG V, LIAU Y C., Modeling of HMX/GAP pseudopropellant combustion, Combustion and Flame, 131, 3, pp. 227-245, (2002)
  • [8] PALETSKY A A, KOROBEINICHEV O P, TERESHCHENKO A G, Et al., Flame structure of HMX/GAP propellant at high pressure, Proceedings of the Combustion Institute, 30, 2, pp. 2105-2112, (2005)
  • [9] GLOTOV O G., Condensed combustion products of aluminized propellants. IV. Effect of the nature of nitramines on aluminum agglomeration and combustion efficiency, Combustion Explosion & Shock Waves, 42, 4, pp. 436-449, (2006)
  • [10] LIU H, AO W, LIU P, Et al., Experimental investigation on the condensed combustion products of aluminized GAP‑based propellants, Aerospace Science and Technology, 97, (2019)
123