Page 27 - 《含能之美》2019封面论文

209
管 状 发 射 药 内 孔 侵 蚀 燃 烧 与 流 动 特 性
［6］ Char J M，Kuo K. Study of combustion processes of single⁃per⁃ XU Han⁃tao，XIAO Zheng⁃gang，HE Wei⁃dong. Combustion
characteristics of partially cut multi⁃perforated stick propellant
forated stick propellants［J］. Journal of Propulsion and Power，
1987，5（3）：262-268. ［J］. Chinese Journal of Energetic Materials（Hanneng Cailiao），
［7］ Hsieh W H，KUO K. Erosive and strand burning of stick pro⁃ 2014，22（2）：251-255.
pellants. II⁃theoretical modeling of erosive⁃burning processes ［13］ Xiao Z，Xu F. Relationship between slivering point and gas
［J］. Journal of Propulsion and Power，1990，6（4）：400-406. generation rules of 19⁃perforation TEGDN propellants with dif⁃
［8］ Char Jir⁃Ming. A study of flame spreading，combustion，and ferent length/outside diameter ratios and perforation diameters
fracture of single⁃perforated stick propellants［D］. Pennsylva⁃ ［J］. Journal of Energetic Materials，2016，36（2）：141-151.
nia：The Pennsylvania State University，1987. ［14］ 张小兵，金志明 . 枪炮内弹道学［M］. 北京：北京理工大学出版
［9］ 张柏生 . 炮药侵蚀燃烧的理论分析［J］. 华东工学院学报，1986， 社，2014：14-18 ．
10（2）：73-87. ZHANG Xiao⁃bing，JIN Zhi⁃ming. Interior ballistics of guns
ZHANG Bai⁃sheng. Theoretical analysis of erosive burning for ［M］. Beijing：Beijing Institute of Technology Press， 2014：
gun propellants［J］. Journal of East China Institute of Technolo⁃ 14-18 ．
gy，1986，10（2），73-78. ［15］ 何洪庆 . 固体火箭发动机气体动力学［M］. 西安：西北工业大学
出版社，1988：28-32.
［10］ 杨丰友 . 太根发射药侵蚀燃烧效应研究［D］. 南京：南京理工大
学，2013. HE Hong⁃qing. Aerodynamics of solid rocket motor［M］.
YANG Feng⁃you. The research of the erosive burning effect on Northwestern Polytechnical University Press，1988：28-32.
TEGN propellant［D］. Nanjing：Nanjing University of Science ［16］ Mukunda S H，Paul J P. Universal behaviour in erosive burn⁃
and Technology，2012. ing of solid propellants［J］. Combustion and Flame. 1997，109
［11］ Xiao Z，Xu H，He W. Influence of venting parameters on ero⁃ （1-2）：224-236.
sive burning of partially cut multi⁃perforated stick propellants ［17］ 王志健，杜佳佳 . 动网格在固体火箭发动机非稳态工作过程中的
［J］. Science and Technology of Energetic Materials，2015，76 应用［J］. 固体火箭技术 . 2008，31（4）：350-353.
（1）：42-46. WANG Zhi⁃jian，DU Jia⁃jia. Application of dynamic mesh to
unsteady burning of solid rocket motor［J］. Journal of Solid
［12］ 徐汉涛，肖正刚，何卫东 . 部分切口多孔杆状发射药的燃烧性能
［J］. 含能材料 . 2014，22（2）：251-255. Rocket Technology，2008，31（4）：350-353.

Internal Perforation Erosive Burning and Flow Characteristics of Tubular Propellant

ZHAO Xiao⁃liang，ZHANG Xiao⁃bing
（School of Energy and Power Engineering，Nanjing University of Science and Technology，Nanjing 210094，China）
Abstract：To study the characteristics of erosive burning and gas flow in internal perforation of a tubular propellant，an interior
ballistic model of a closed bomb was established considering the gas phase region inside the tube，gas phase region outside the
tube and solid propellant region. The accuracy of the interior ballistic model and calculation method of the closed bomb was ver⁃
ified through comparing the numerical simulation results with the experimental data in the literature. On this basis，the effects of
different length，internal diameter and loading density of propellant on the erosive burning of internal perforation were discussed
respectively. Results show that for the tubular propellant with d=0.56 mm，l=50 mm，when 0.016 ≤ ψ ≤ 0.80（ψ is the burned
percentage），the maximum pressure difference of internal and external perforation increases from 1.23 MPa to 2.00 MPa，the
maximum gas velocity on the end face decreases from 430 m·s -1 to 200 m·s ，the erosive burning coefficient on the end face
-1
decreases from 1.98 to 1.10，the erosive burning critical point of internal perforation moves from 7mm away from the symmetri⁃
cal plane to 20 mm，the erosive burning area decreases by 65%. The ratio of burning surface to port area is an important factor
affecting the erosive burning of internal perforation. The erosive burning does not occur when the ratio of burning surface to port
area is less than 71.4. The erosive burning intensity becomes stronger with the increase of length and decrease of internal diame⁃
ter，i.e. with the increase of the ratio of burning surface to port area，the erosive burning occurs evidently when the ratio of burn⁃
ing surface to port area is larger than 142.8. The maximum gas velocity on the end face and the erosive burning coefficient de⁃
crease slightly as the loading density increases，while the gas pressure difference of internal and external perforation increases ob⁃
viously.
Key words：tubular propellant；closed bomb；gas flow in internal perforation；erosive burning；numerical simulation
CLC number：TJ012.1 Document code：A DOI：10.11943/CJEM2018080

（责编 王艳秀）

CHINESE JOURNAL OF ENERGETIC MATERIALS 含能材料 2019 年 第 27 卷 第 3 期 （202-209）