装药结构对固体火箭发动机烤燃温度分布的影响

杨筱; 智小琦; 杨宝良; 李娟娟

doi:10.11858/gywlxb.2017.04.012

装药结构对固体火箭发动机烤燃温度分布的影响

doi: 10.11858/gywlxb.2017.04.012

1.
中北大学地下目标毁伤技术国防重点学科实验室，山西太原 030051
2.
西安现代控制技术研究所，陕西西安 710065
3.
晋西工业集团有限责任公司，山西太原 030027

详细信息

作者简介:
杨筱(1990—), 男，硕士研究生，主要从事弹药易损性研究.E-mail:420381yx@sina.com

中图分类号: O382.3; TJ55
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出版历程
- 收稿日期: 2016-11-17
- 修回日期: 2017-04-02

Influence of Charge Structure on the Cook-off Temperature Distribution of Solid Rocket Motor

1.
National Defense key Laboratory of Underground Damage Technology, North University of China, Taiyuan 03005, China
2.
Xi'an Modern Control Technology Research Institute, Xi'an 710065, China
3.
Jinxi Industries Group Co., Ltd, Taiyuan 030027, China

摘要

摘要: 为研究装药结构对固体火箭发动机烤燃特性的影响，以装填HTPE推进剂的固体火箭发动机为研究对象，建立了复合、单孔管形及星孔形3种装药结构的固体发动机烤燃模型。以1和2℃/min的升温速率对小尺寸HTPE推进剂烤燃试样进行烤燃实验，以实验结果为基础，修正了推进剂材料参数。利用Fluent软件对3种装药结构在不同升温速率(β)下的烤燃行为进行了数值模拟。结果表明：装药结构对固体火箭发动机的烤燃响应时间、点火点和快/慢速烤燃的划分都有影响; 星孔形装药会导致点火点出现跳跃性变化的临界升温速率效应，而单孔管形装药不存在此现象。在本研究条件下，包含星孔段的复合装药发动机的临界升温速率为0.2℃/min，星孔形装药发动机的临界升温速率为0.3和0.5℃/min，即当0.3℃/min≤β≤0.5℃/min时点火点发生跳跃变化。
- 固体火箭发动机 /
- 装药结构 /
- HTPE推进剂 /
- 数值模拟
Abstract: To investigate the influence of the charge structure on the cook-off characteristics of the solid rocket motor, we established 3 simplified cook-off models with 3 different charge structures, including the composite, the mono tube and the star tube, for the solid rocket motor with HTPE propellant.We conducted a cook-off test of small-size cook-off samples with HTPE propellant at the heating rate of 1℃/min and 2℃/min, and based on this experiment result, we adjusted the parameters of propellant material.By using the FLUENT software, we conducted the numerical simulation of the models' cook-off behaviors with 3 different charge structures at different heating rates (β).The results show that the charge structure has influence on the cook-off response time, the ignition point and the fast or slow cook-off division.The star tube charge leads to a critical heating rate effect, i.e. the jumping change of the ignition point, whereas the mono tube charge does not.Under the condition of this study, the critical heating rate of the composite charge motor with a star tube section is 0.2℃/min, and the critical heating rate of the star tube charge motor is 0.3 and 0.5℃/min, that is, when 0.3℃/min≤β≤0.5℃/min the ignition point jump changes.
- solid rocket motor /
- charge structure /
- HTPE propellant /
- numerical simulation

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图 1 小尺寸烤燃试样

Figure 1. Small-size cook-off sample

下载: 全尺寸图片幻灯片

图 2 烤燃试样实验后状态

Figure 2. Status of cook-off sample after experiment

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图 3 烤燃实验响应时刻的温度云图

Figure 3. Temperature distribution of cook-off test at response time

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图 4 不同装药结构的固体火箭发动机结构

Figure 4. Solid rocket motor with 3 different charge structures

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图 5 3种装药结构发动机的烤燃物理模型

Figure 5. Models of rocket motor with 3 charge structures

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图 6 升温速率为0.1、0.2、0.3、0.5℃/min时复合装药发动机在烤燃响应时刻的温度云图

Figure 6. Temperature distribution of motor with composite charging at response time when β=0.1, 0.2, 0.3, 0.5℃/min

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图 7 升温速率为0.2、0.3、0.5、0.6℃/min时星孔形装药发动机在烤燃响应时刻的温度云图

Figure 7. Temperature distribution of motor with star tube charging at response time when β=0.2, 0.3, 0.5, 0.6℃/min

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图 8 升温速率为0.055、0.5、2.0℃/min时单孔管形装药发动机在烤燃响应时刻的温度云图

Figure 8. Temperature distribution of motor with mono tube charging at response time when β=0.055, 0.5, 2.0℃/min

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表 1 HTPE推进剂烤燃实验结果

Table 1. Experiment result of cook-off of HTPE propellant

β/ (℃/min)	t_r/ (min)	T_r/ (℃)
1	139.8	165.0
2	73.3	171.6

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表 2 推进剂材料参数

Table 2. Material parameters of HTPE propellant

ρ/ (kg/m³)	c_V/ (J/(kg·K))	λ/ (J/(m·K·s))	Q/ (MJ/kg)	A/ (s^-1)	E/ (kJ/mol)	R/ (J/(mol·K))
1726	840	0.42	6.348	7.25×10⁸	114.261	8.314

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表 3 小尺寸试样仿真结果

Table 3. Simulation results of small-size sample

β/(℃/min)	t_r/(min)	T_r/(℃)	Temperature of ignition/(℃)	δ_t/(%)
1	141.00	166.00	232.50	0.86
2	72.23	169.46	231.64	1.50
Note:δ_t is the relative error of response time (t_r).

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表 4 材料的物性参数

Table 4. Physical parameters of materials

Material	ρ/ (kg/m³)	c_V/ (J/(kg·K))	λ/ (J/(m·K·s))
Case	7850	480	43
Insulation	870	1670	0.22
Air	1.225	1006.43	0.0242

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表 5 不同升温速率下固体火箭发动机烤燃计算结果

Table 5. Results of cook-off of solid rocket motor at different heating rates

β/ (℃/min)	Composite		Mono tube		Star tube
β/ (℃/min)	t_r/(h)	T_r/(℃)	t_r/(h)	T_r/(℃)	t_r/(h)	T_r/(℃)
0.055	28.83	120.13	28.77	119.95	29.10	121.00
0.083	19.72	123.62	19.71	123.53	19.85	124.27
0.1	16.75	125.51	16.74	125.45	16.78	125.65
0.5	4.21	151.24	4.23	151.79	4.25	152.45
1.0	2.32	164.27	2.33	164.33	2.36	166.73
1.5	1.64	172.48	1.65	172.50	1.67	175.15
2.0	1.28	178.68	1.29	178.73	1.30	180.83

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表 6 不同升温速率下发动机烤燃点火位置

Table 6. Ignition positions of cook-off at different heating rates

β/ (℃/min)	Composite		Mono tube		Star tube
β/ (℃/min)	l/(mm)	r/(mm)	l/(mm)	r/(mm)	l/(mm)	r/(mm)
0.055	919.5-936.5	8	214.0-254.0	5	73-95	4.3
0.1	932.0-954.0	8	123.5-135.0	5	69-102	4.3
0.5	12.1-16.3	40	10.0-18.0	41	1290-1315	42.6
1.0	5.0-9.6	47	3.1-11.5	47	5-9	48.8
1.5	2.2-7.2	49	1.1-8.9	49	1-7	50.0
2.0	0-5.7	50	0-8.0	50	0-6	50.7
Note:l is the axial distance to the front face of the propellant grain, r is the radial distance to the internal surface of the propellant grain.

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参考文献(13)

[1]	Military standard-hazard assessment tests for non-nuclear munitions: MIL-STD-2105C[S]. 2003.
[2]	HO S Y.Thermomechanical properties of rocket propellants and correlation with cook-off behavior[J]. Propell Explos Pyrot, 1995, 20(4):206-214. doi: 10.1002/prep.19950200409/full
[3]	CARO R I, BELLERBY J M.Behavior of hydroxyl-terminated polyether (HTPE) composite rocket propellants in slow cook-off[J]. Int J Energ Mater Chem Propul, 2008, 7(3):171-185.
[4]	赵孝彬, 李军, 程立国, 等.固体推进剂慢速烤燃特性的影响因素研究[J].含能材料, 2011, 19(6):669-672. doi: 10.3969/j.issn.1006-9941.2011.06.016 ZHAO X B, LI J, CHENG L G, et al.Influence factors of slow cook-off characteristic for solid propellant[J]. Chinese Journal of Energetic Materials, 2011, 19(6):669-672. doi: 10.3969/j.issn.1006-9941.2011.06.016
[5]	陈晨, 路桂娥, 江劲勇, 等.GATo-3推进剂的烤燃实验[J].含能材料, 2015, 23(6):563-567. http://d.old.wanfangdata.com.cn/Periodical/hncl201506011 CHEN C, LU G E, JIANG J Y, et al.Cook-off test of GATo-3 propellant[J]. Chinese Journal of Energetic Materials, 2015, 23(6):563-567. http://d.old.wanfangdata.com.cn/Periodical/hncl201506011
[6]	原渭兰, 潘浪.一种舰载导弹固体火箭发动机烤燃过程的数值计算方法[J].舰船科学技术, 2009, 31(7):129-132. doi: 10.3404/j.issn.1672-7649.2009.07.029 YUAN W L, PAN L.An numerical calculation method on cook-off of solid rocket motor of ship-based missiles[J]. Ship Science and Technology, 2009, 31(7):129-132. doi: 10.3404/j.issn.1672-7649.2009.07.029
[7]	杨后文, 余永刚, 叶锐.AP/HTPB复合固体推进剂慢烤燃特性的数值模拟[J].含能材料, 2015, 23(10):924-929. doi: 10.11943/j.issn.1006-9941.2015.10.002 YANG H W, YU Y G, YE R.Numerical simulation of slow cook-off characteristic for AP/HTPB composite solid propellant[J]. Chinese Journal of Energetic Materials, 2015, 23(10):924-929. doi: 10.11943/j.issn.1006-9941.2015.10.002
[8]	杨后文, 余永刚, 叶锐.不同火焰环境下固体火箭发动机烤燃特性数值模拟[J].兵工学报, 2015, 36(9):1640-1646. doi: 10.3969/j.issn.1000-1093.2015.09.006 YANG H W, YU Y G, YE R.Numerical simulation of cook-off characteristic of solid rocket motor in different flame environments[J]. Acta Armamentarii, 2015, 36(9):1640-1646. doi: 10.3969/j.issn.1000-1093.2015.09.006
[9]	丁黎, 王琼, 王江宁, 等.高固含量改性双基推进剂的烤燃试验研究[J].固体火箭技术, 2014, 37(6):829-837. http://d.old.wanfangdata.com.cn/Periodical/gthjjs201406017 DING L, WANG Q, WANG J N, et al.Study of screw extrusion modified double base (MDB) propellant with high solid congtent by cook-off test[J]. Journal of Solid Rocket Technology, 2014, 37(6):829-837. http://d.old.wanfangdata.com.cn/Periodical/gthjjs201406017
[10]	冯长根.热爆炸理论[M].北京:科学出版社, 1988. FENG C G.Thermal explosion theory[M]. Beijing:Science Press, 1988.
[11]	王福军.计算流体动力学[M].北京:清华大学出版社, 2004. WANG F J.Analysis of computational fluid dynamics[M]. Beijing:Tsinghua University Press, 2004.
[12]	Fluent Inc.FLUENT user's guide[Z]. US: Fluent Inc, 2006.
[13]	陈朗, 马欣, 黄毅民, 等.炸药多点测温烤燃实验和数值模拟[J].兵工学报, 2011, 32(10):1230-1236. http://d.old.wanfangdata.com.cn/Periodical/bgxb201110010 CHEN L, MA X, HUANG Y M, et al.Multi-point temperature measuring cook-off test and numerical simulation of explosive[J]. Acta Armamentarii, 2011, 32(10):1230-1236. http://d.old.wanfangdata.com.cn/Periodical/bgxb201110010