Analysis of Interior Ballistic Characteristics of Conical Three-Dimensional Charge Column Under Lateral Overload

doi:10.12382/bgxb.2022.0162

Abstract

Abstract:

The occurrence of internal ballistic anomalies during high-altitude missile maneuvering can result in flight mission failures. To analyze the abnormal mechanism of internal ballistics, the internal ballistics characteristics of motor under lateral overload were studied. Experimental measurements of the burning rate of HTPB ternary propellant under overload conditions were conducted, and a burning rate model of the propellant under overload was established. Based on this model, the non-uniform combustion surface retreat of cone-hole grain was simulated. The interior ballistic characteristics of cone-hole grain under three overload modes, namely, full lateral overload, short-time constant lateral overload, and short-time oscillation lateral overload, were studied. The results show that lateral overload increases the pressure in the combustion chamber and accelerates the exposure time of the insulation layer. The pressure oscillation frequency produced by oscillating overload is consistent with that of overload oscillation. Instantaneous lateral overload leads to a transitional increase in combustion chamber pressure. Under 100g overload, the pressure increases by about 8%, the overload disappears, and the pressure plummets. When the lateral overload time interval is constant, stable pressure conditions are advantageous for missile maneuvering under overload conditions.

Key words: conical three-dimensional cylinder, burning rate, burning surface retreat, lateral overload, interior ballistics

TIAN Zhongliang, LI Junwei, HE Ye, XU Tuanwei, DING Miao, WANG Ningfei. Analysis of Interior Ballistic Characteristics of Conical Three-Dimensional Charge Column Under Lateral Overload[J]. Acta Armamentarii, 2023, 44(7): 1896-1907.

Figures/Tables 20

Fig.1 Schematic diagram of the structure and dimensions of the grain

Fig.2 Schematic diagram of the combustion process

Fig.3 Schematic diagram of the retreat of the combustion surface

Fig.4 Schematic diagram of the retreat of the combustion surface with lateral overload

Fig.5 Partial enlarged view of the retreat of internal combustion surface from t1 to t1+Δt

Fig.6 Solving element of burning surface at time t1

Fig.7 Burning surface shape at t1

Fig.8 Calculation of the motor size

Fig.9 Internal ballistics calculation process

Fig.10 Comparison of parallel layer retreat of 3D software and this paper

Fig.11 Comparison between the experimental results and calculations in this paper

Fig.12 Relationship between the rate of increasing burning rate and the magnitude of overload and azimuth

Table 1 30g, 50g three-dimensional combustion surface retreat process

Fig.13 Internal ballistic characteristic diagram with lateral overload

Fig.14 Comparison of percent pressure increase, thermal insulation exposure time, and specific impulse

Fig.15 Variation of burning meat thickness with time in Section A and right section

Fig.16 Internal ballistic characteristics of overload applied during t=6-9s

Fig.17 Data comparison of applied lateral overload in four time periods

Fig.18 Influence of oscillation overload on internal ballistic characteristics

Fig.19 Comparison of pressure oscillation and overload oscillation

References 23

[1]	唐金兰, 刘佩进. 固体火箭发动机原理[M]. 北京: 国防工业出版社, 2012:251-253.
	TANG J L, LIU P J. Principle of solid rocket motor[M]. Beijing: National Defense Industry Press, 2012:251-253. (in Chinese)
[2]	CROWE C T, WILLOUGHBY P G. Effect of spin on the internal ballistics of a solid propellant motor[C]//Proceedings of Aerospace Sciences Meeting.New York, NY, US:AIAA,1966.
[3]	BAKER K L, CRIWE C T, WILLOUGHBY P G. A photographic and analytic study of composite propellant combustionin an acceleration field[J]. Journal of Spacecraft & Rockets, 1971, 8(4):310-317.
[4]	WILLOUGHBY P G, CROWE C T, BAKER K L. A photogr-aphic and analytic study of composite propellant Co-mbustion in an acceleration field[J]. Spacecraft, 1971, 8(4):310-317.
[5]	GLICK R L. An analytical study of the effects of radial acceleration upon the combustion mechanism of solid propellant final report:NASA-CR-66218[R]. Washington, D.C., US: NASA, 1966.
[6]	NORTHAM G B. Effects of steady-state acceleration on combustion characteristics of an aluminized composite solid propellant[J]. Speculum, 1969, 44(6):1-41. doi: 10.2307/2855034 URL
[7]	GREATRIX D R, GOTTLIEB J. Model for prediction of normal acceleration augmentation of composite-propellant combustion[J]. Mental Retardation, 1987, 7(2):3-6.
[8]	GREATRIX D R. Acceleration-based combustion augmen-tation modelling for noncylindrical grain solid rocket motors[C]//Proceedings of Joint Propulsion Conference & Exhibit.San Diego,CA, US:AIAA, 1995.
[9]	GREATRIX D R. Powered flight the engineering of aerospace Propulsion[M]. London,UK:Springer, 2012:371-373.
[10]	包轶颖, 赵瑜, 丁逸夫, 等. 横向加速度下固体火箭燃面推移规律[J]. 固体火箭技术, 2016, 39(1):23-27.
	BAO Y Y, ZHAO Y, DING Y F, et al. Solid propellant grain motion under lateral acceleration[J]. Journal of Solid Rocket Technology, 2016, 39(1):23-27. (in Chinese)
[11]	官典, 李世鹏, 刘筑, 等. 横向过载对固体火箭发动机推进剂点火建压过程的影响[J]. 兵工学报, 2021, 42(9):1877-1887. doi: 10.3969/j.issn.1000-1093.2021.09.008
	GUAN D, LI S P, LIU Z, et al. Influence of lateral acceleretion on ignition transients of solid rocket motor[J]. Acta Armamentarii, 2021, 42(9):1877-1887. (in Chinese)
[12]	GREATRIX D R. A study of combustion and flow behavior in solid-propellant rocket motors[D]. Toronto,Canada: University of Toronto, 1987.
[13]	GREATRIX D R. Correlation of pressure rise with radial vibration level in solid rocket motors[C]//Proceedings of Joint Propulsion Conference & Exhibit.San Diego,CA,US:AIAA,1995.
[14]	GREATRIX D R, HARRIS P G. Structural vibration consi-derations for solid rocket internal ballistics modeling[C]//Proceedings of AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Las Vegas,NV,US:AIAA, 2000.
[15]	李桢, 王中伟, 张为华, 等. 横向过载下固体火箭发动机内弹道仿真[J]. 弹箭与制导学报, 2005, 25(4):726-728,732.
	LI Z, WANG Z W, ZHANG W H, et al. Internal ballistic simulation of solid rocket engine under lateral overload[J]. Journal of Missile and Guidance, 2005, 25(4):726-728,732. (in Chinese)
[16]	曹军, 郭颜红, 邢强. 高过载条件下固体火箭发动机工作稳定性研究[J]. 航空兵器, 2014, 51(1):33-36.
	CAO J, GUO Y H, XING Q. Research on the working stability of solid rocket engine under high overload[J]. Aviation Weapons, 2014, 51(1):33-36. (in Chinese)
[17]	郭颜红, 梁晓庚, 陈斌. 大过载下固体火箭发动机内弹道计算[J]. 航空动力学报, 2008, 23(10):1944-1948.
	GUO Y H, LIANG X G, CHEN B. Internal ballistic calculation of solid rocket engines under large overload[J]. Journal of Aerodynamics, 2008, 23(10):1944-1948. (in Chinese)
[18]	郭颜红, 梁晓庚, 陈斌. 大过载下固体火箭发动机工作过程仿真的数学模型[J]. 航空兵器, 2008, 45(1):21-25.
	GUO Y H, LIANG X G, CHEN B. Working process simulation of solid rocket motor with high acceleration load[J]. Aero Weaponry, 2008, 45(1):21-25. (in Chinese)
[19]	刘中兵, 郜伟伟, 张飞. 飞行过载对固体发动机内弹道的影响[J]. 固体火箭技术, 2018, 41(2):169-175.
	LIU Z B, GAO W W, ZHANG F. Influence of aeecleration on internal ballistics of solid rocker motor[J]. Journal of Solid Rocket Technology, 2018, 41(2):169-175. (in Chinese)
[20]	檀叶, 何景轩, 孙展鹏. 过载条件下固体火箭发动机燃烧稳定性分析[J]. 弹箭与制导学报, 2015, 35(3):113-116.
	TAN Y, HE J X, SUN Z P. Combustion Stability analysis for solid rocket motor under overload[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2015, 35(3):113-116. (in Chinese)
[21]	张翔宇, 高波, 甘晓松, 等. 飞行过载对固体火箭发动机不稳定燃烧的影响[J]. 宇航学报, 2019, 40(8):972-976.
	ZHANG X Y, GAO B, GAN X S, et al. Impacts of flight acceleration on combustion instability of solid rocket motor[J]. Journal of Astronautics, 2019, 40(8):972-976. (in Chinese)
[22]	贺业, 李军伟, 田忠亮, 等. 过载条件下高铝粉含量丁羟复合推进剂燃烧性能试验研究[C]//中国宇航学会固体火箭推进专业委员会第38届学术年会论文集.遵义, 贵州: 中国宇航学会, 2021:494-500.
	HE Y, LI J W, TIAN Z L, et al. Experimental study on the combustion performance of high aluminum content HTPB composite propellants under overload conditions[C]//Proceedings of the 38th Academic Annual Meeting of the Solid Rocket Propulsion Professional Committee of the Chinese Aerospace Society. Zunyi, Guizhou: Chinese Aerospace Society, 2021:494-500.
[23]	万章吉, 商晨燕, 曹泰岳. 加速度对固体发动机内弹道性能影响的实验研究[J]. 固体火箭技术, 1991(3):24-30.
	WAN Z J, SHANG C Y, CAO T Y. Experimental study on the influence of acceleration on internal ballistic performance of solid motor[J]. Solid Rocket Technology, 1991(3):24-30. (in Chinese)