主控提前点火对复合推进剂慢速烤燃响应的影响

张海军; 聂建新; 王领; 王栋; 胡峰; 郭学永

doi:10.11883/bzycj-2021-0521

主控提前点火对复合推进剂慢速烤燃响应的影响

doi: 10.11883/bzycj-2021-0521

张海军^1,,
聂建新^1, ,,
王领²,
王栋²,
胡峰²,
郭学永¹

1.
北京理工大学爆炸科学与技术国家重点实验室，北京 100081
2.
西安长峰机电研究所，陕西西安 710065

基金项目: 国家自然科学基金（11772058）

详细信息

作者简介:
张海军（1992－　），男，博士研究生，zhj9209@163.com

通讯作者:
聂建新（1977－　），男，博士，副研究员，niejx@bit.edu.cn

中图分类号: O389
计量
- 文章访问数: 440
- HTML全文浏览量: 145
- PDF下载量: 79
- 被引次数: 0
出版历程
- 收稿日期: 2021-12-20
- 修回日期: 2022-05-12
- 网络出版日期: 2022-05-20
- 刊出日期: 2022-10-31

Effect of pre-ignition on slow cook-off response characteristics of composite propellant

1.
State Key Laboratory of Explosion Science and Technology, Beijing Institute of Technology, Beijing 100081, China
2.
Xi’an Changfeng Research Institute of Mechanical-electrical, Xi’an 710065, Shaanxi, China

摘要

摘要: 为研究主控点火对复合推进剂慢速烤燃响应特性的影响，设计并开展了典型复合推进剂装药慢速烤燃实验，结合数值计算和推进剂热分解失重及形貌演化过程，探讨了点火前推进剂内的温度分布情况及推进剂细观结构热损伤规律。研究发现：针对复合推进剂装药的慢速烤燃，在推进剂发生自热点火前温度较低时进行主控点火可以有效降低反应剧烈程度；随着加热温度的升高，推进剂中部分组分发生分解，导致推进剂内部温度高于壳体温度，同时推进剂中粘结剂及AP的分解会导致推进剂装药形成多孔状的结构，在点火后更易导致对流燃烧，加剧反应烈度；当壳体温度仅138 ℃时，推进剂温度最高点达到150 ℃，最高点首先出现在靠近喷管的尾部，考虑到粘结剂及AP部分分解导致的孔隙结构会加剧反应的响应烈度，主控点火温度应设定在138 ℃以下。
- 复合推进剂 /
- 慢速烤燃 /
- 点火温度 /
- 响应特性
Abstract: The study of slow cook-off of composite propellant containing ammonium perchlorate (AP) is the focus of the research on propellant safety, while the pre-ignition is a common and effective way to reduce the intensity of reaction in slow cook-off of engine. To investigate the effect of pre-ignition temperature on its response characteristics, a set of slow cook off experiments of composite propellant was designed and carried out, and the response characteristics of ignition at different temperatures were studied. The temperature distribution of the propellant and the thermal damage law of propellant microstructure before ignition were investigated by numerical simulation and thermal decomposition experiment. The results show that the engine spontaneously ignited with a reaction level of violent explosion, and the reaction level was burning when it was ignited at 120 ℃. The intensity of the reaction could be reduced effectively by pre-ignition when the propellant temperature was low before auto-ignition. The thermal decomposition process and thermal structure damage evolution of the propellant during slow cook-off were studied by thermogravimetry analysis combined with morphological characterization. As the heating temperature increased, some components of the propellant were decomposed, causing the internal temperature of the propellant to be higher than that of the shell, while the breakdown of binders and AP in the propellant resulted in a porous structure of the propellant charge, more likely leading to convection combustion after ignition and increasing the intensity of the reaction. Due to the autothermal reaction of the propellant, the highest temperature of the propellant reached 150 ℃ when the shell temperature was only 138 ℃. The highest temperature first appeared near the tail of the nozzle. Considering the influence of porous structure caused by AP decomposition on the intensity of reaction, the ignition temperature in advance should be lower than 138℃. In order to avoid the decomposition in the propellant to produce porous structure, which would cause severe reaction after ignition, some measures should be taken in igniting the propellant before the main propellant reaches auto-ignition temperature, which can effectively reduce the intensity of reaction.
- composite propellant /
- slow cook-off /
- ignition temperature /
- response characteristic

HTML全文

图 1 慢速烤燃系统及超压传感器布置示意图

Figure 1. Schematic diagram of slow cook-off system

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图 2 实验现场

Figure 2. The experimental site

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图 3 烤燃箱内布置

Figure 3. Layout inside the cook-off oven

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图 4 热电偶布置示意图

Figure 4. Thermocouple arrangement position

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图 5 数值计算模型

Figure 5. The model of numerical calculation

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图 6 实验1中不同位置温度变化曲线

Figure 6. The temperature monitoring data in experiment 1

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图 7 实验2中不同位置温度变化曲线

Figure 7. The temperature monitoring data in experiment 2

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图 8 实验1反应后现场破坏情况

Figure 8. Field damage after reaction in experiment 1

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图 9 实验1超压数据

Figure 9. The shock wave pressure in experiment 1

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图 10 实验2反应后现场破坏情况

Figure 10. Field damage after reaction in experiment 2

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图 11 实验1中监测点5温度实验与数值计算结果对比

Figure 11. Comparison of temperature test and simulation results of monitoring point 5 in experiment 1

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图 12 慢速烤燃过程中温度云图

Figure 12. The temperature nephogram for slow cook-off

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图 13 推进剂药片缓慢加热实验装置

Figure 13. Experimental device for slow heating propellant tablets

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图 14 HTPE推进剂缓慢加热质量及形貌变化过程

Figure 14. Mass fraction and morphological change of HTPE propellant

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图 15 推进剂缓慢加热过程中细观形貌变化

Figure 15. Micromorphological change of propellant during slow cook-off

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图 16 不同温度点火前150 ℃以上推进剂的分布

Figure 16. Distribution of propellants above 150 ℃ before ignition at different temperatures

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图 17 150℃以上推进剂占比随烤燃温度变化

Figure 17. Proportion of propellant above 150 ℃ varying with cook-off temperature

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表 1 烤燃件材料参数^[9]

Table 1. Material parameters of cook-off components^[9]

材料	密度/（kg·m⁻³）	比热容/（J·kg⁻¹·℃⁻¹）	热导率/（W·m⁻¹·℃⁻¹）	指前因子/s⁻¹	活化能/(kJ·mol⁻¹)	分解热/(kJ·kg⁻¹)
壳体	8 030	502.48	16.27
绝热层	1 222	1 998	0.226
空气	1.225	1006.43	0.0242
推进剂	1 740	1 700	0.214	2.7536×10¹¹	140.0	6 348

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