活性弹丸超高速撞击蜂窝夹芯板双层结构的损伤特性

任思远; 武强; 张品亮; 宋光明; 陈川; 龚自正; 李正宇

doi:10.11883/bzycj-2023-0272

活性弹丸超高速撞击蜂窝夹芯板双层结构的损伤特性

doi: 10.11883/bzycj-2023-0272

任思远^1,,
武强^{1, 2, ,},
张品亮¹,
宋光明¹,
陈川¹,
龚自正^{1, 2},
李正宇¹

1.
北京卫星环境工程研究所，北京100094
2.
可靠性与环境工程技术国防科技重点实验室，北京100094

基金项目: 国家自然科学基金（12202068）；国防科工局空间碎片专项（KJSP2023020201, KJSP2020010402）

详细信息

作者简介:
任思远（1988－　），男，博士，工程师，yuandermail@yeah.net

通讯作者:
武　强（1987－　），男，博士，高级工程师，wuqiang12525@126.com

中图分类号: O385
计量
- 文章访问数: 91
- HTML全文浏览量: 29
- PDF下载量: 70
- 被引次数: 0
出版历程
- 收稿日期: 2023-08-02
- 修回日期: 2024-04-11
- 网络出版日期: 2024-04-28
- 刊出日期: 2024-07-15

A study of damage characteristics caused by hypervelocity impact of reactive projectile on the honeycomb sandwich panel double-layer structure

1.
Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China
2.
Science and Technology on Reliability and Environmental Engineering Laboratory, Beijing 100094, China

摘要

摘要: 为了研究蜂窝夹芯板双层结构在活性弹超高速撞击下的损伤特性，制备了PTFE（polytetrafluoroethylene）/Al/Cu柱形活性弹丸，利用二级轻气炮对蜂窝夹芯板双层结构靶开展超高速撞击实验，采用超高速摄像机记录了活性弹撞击蜂窝板的碎片云演化过程，分析了蜂窝板的穿孔特性和结构内部各组件的损伤特征；数值模拟了撞击过程，分析了活性弹丸的超高速侵爆效应，获得了碎片云的膨胀运动规律，揭示了活性弹丸冲击-爆轰耦合效应对靶板的损伤机理。结果表明：活性弹丸在蜂窝板上形成较小的入射孔和较大的出射孔，出射孔直径随着撞击速度的提高而增大；蜂窝夹芯板入射孔、出射孔和蜂窝芯穿孔直径随着活性弹体质量的增加而增大，入射孔直径不受蜂窝板厚度和蜂窝芯胞格直径的影响，出射孔和蜂窝芯穿孔直径随着蜂窝板厚度的增大先增大后减小，随着蜂窝芯胞格直径的增大而增大；活性弹产生具有较高膨胀速度的高温碎片云，其膨胀速度随着撞击速度的提高而提高。活性弹的冲击-爆轰耦合效应增大了结构内部组件的毁伤面积。在2~6 km/s速度范围内，活性弹在蜂窝板上形成的出射孔直径约为铝合金弹的1.3~1.8倍，碎片云的膨胀速度是铝合金弹的1.8~3.2倍。相较于铝合金弹丸，活性弹丸增大了蜂窝夹芯板双层结构内部和后板的毁伤面积，提高了毁伤效能。
- 活性弹丸 /
- 超高速撞击 /
- 碎片云 /
- 损伤特征 /
- 冲击-爆轰耦合效应
Abstract: With the prepared reactive projectiles, and the two-stage light gas gun was used to conduct hypervelocity impact experiments on the honeycomb double-layer structure target. A high-speed camera was used to record the impact process, so the evolution process of debris clouds during the impact of the reactive projectile on honeycomb panels was obtained. By recycling the targets, the perforation characteristics of the honeycomb plate were analyzed, and the damage characteristics of various components inside the structure were found. Numerical simulations of impact process are carried out, and the hypervelocity penetration effect of reactive projectiles is analyzed according to the experimental and numerical simulation results. The expansion motion law of debris clouds is obtained, revealing the damage mechanism of the coupling effect of impact-detonation of reactive projectiles on the target. The results indicate that the impact initiation characteristic of reactive projectile can form smaller inlet and larger outlet holes on honeycomb panel, and the diameter of the outlet perforation increases with the increase of impact velocity. Under the impact of reactive projectile, the perforation diameters of honeycomb sandwich panel for the entry perforation, exit perforation and honeycomb core perforation all increase with the increase of reactive projectile mass. The perforation diameters are not affected by the thickness of honeycomb sandwich panel. The perforation diameter and honeycomb core perforation diameter first increase and then decrease with the increase of honeycomb panel thickness. The entry perforation does not change with the increase of honeycomb core cell diameter. The exit perforation diameter and honeycomb core perforation increase with the increase of honeycomb core cell diameter. Reactive projectile can generate high-temperature debris cloud with higher expansion velocity, and the expansion velocity increases with the increase of impact velocity. The coupling effect of impact-detonation of reactive projectile leads to increase of the damage area on the internal components of the target. In the velocity range of 2–6 km/s, the diameter of the perforation hole formed by the reactive projectile on the honeycomb sandwich panel is about 1.3–1.8 times that of the aluminum alloy projectile, and the expansion velocity of the debris cloud is 1.8–3.2 times that of the aluminum alloy projectile. Compared with the aluminum alloy projectile, the reactive projectile increases the damage area of the debris cloud on the inner and rear plates of the honeycomb sandwich panel double-layer structure, and improves the damage efficiency.
- reactive projectile /
- hypervelocity impact /
- debris cloud /
- damage characteristics /
- coupling effect of impact-detonation

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图 1 各组分的质量分数对PTFE/Al/Cu活性弹能量密度和密度的影响

Figure 1. Influences of mass fraction of Cu on energy density and density of PTFE/Al/Cu

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图 2 烧结温度曲线与制备的PTFE/Al/Cu活性材料试件

Figure 2. Sintering temperature curve and sintered specimens of PTFE/Al/Cu reactive material

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图 3 活性材料的动态应力-应变曲线

Figure 3. Dynamic stress-strain curves of reactive materials

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图 4 超高速撞击实验的示意图

Figure 4. Schematic diagram of hypervelocity impact experiment

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图 5 实验用的活性弹丸和蜂窝板双层结构靶

Figure 5. Reactive projectile, sabot, and target used in experiment

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图 6 蜂窝夹芯板入射孔实验结果

Figure 6. Front perforation of honeycomb sandwich panels

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图 7 蜂窝夹芯板出射孔实验结果

Figure 7. Back perforation of honeycomb sandwich panels

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图 8 实验2中高温碎片云的演化过程

Figure 8. Evolution process of high-temperature debris cloud in Exp. 2

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图 9 实验2中后板的破坏结果

Figure 9. Damage results of the rear wall in Exp. 2

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图 10 铝合金弹丸撞击蜂窝夹芯板穿孔的数值模拟结果

Figure 10. Numerical simulation results of perforation of aluminum alloy projectiles impacting honeycomb sandwich panels

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图 11 活性弹丸撞击蜂窝夹芯板穿孔的数值模拟结果

Figure 11. Numerical simulation results of perforation of reactive projectiles impacting honeycomb sandwich panels

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图 12 铝合金弹和活性弹撞击下蜂窝板的动能变化

Figure 12. Kinetic energy change of honeycomb sandwich panel impacted by aluminum alloy projectile and reactive projectile

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图 13 弹丸撞击后蜂窝夹芯板穿孔直径与撞击速度的关系

Figure 13. Relationship between perforation diameter and impact velocity for honeycomb sandwich panels impacted by projectiles

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图 14 弹体质量、蜂窝夹芯板厚度和蜂窝芯胞格直径对穿孔de 影响

Figure 14. Influences of projectile mass, honeycomb sandwich panel thickness and honeycomb core diameter on perforation

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图 15 铝合金弹丸以3 km/s的速度撞击18 mm厚蜂窝夹芯板的温度云图

Figure 15. Temperature cloud maps of an 18-mm-thick honeycomb sandwich panel impacted by an aluminum alloy projectile with the velocity of 3 km/s

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图 16 活性弹丸以3 km/s的速度撞击18 mm厚蜂窝夹芯板的温度云图

Figure 16. Temperature cloud maps of an 18-mm-thick honeycomb sandwich panel impacted by a reactive projectile with the velocity of 3 km/s

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图 17 弹丸撞击后蜂窝夹芯板的碎片云速度与撞击速度的关系

Figure 17. Relationship between the debris cloud velocity and impact velocity for a projectile impacting a honeycomb sandwich panel

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图 18 铝合金弹丸撞击蜂窝夹芯板双层结构的后板损伤结果

Figure 18. Damage results of the rear wall of the honeycomb sandwich panel double-layer structures impacted by aluminum alloy projectiles

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图 19 活性弹丸撞击蜂窝夹芯板双层结构的后板损伤结果

Figure 19. Damage results of the rear wall of the honeycomb sandwich panel double-layer structures impacted by reactive projectiles

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表 1 实验结果

Table 1. Experimental results

编号	弹体			靶板
	材料	尺寸/mm	速度/(km·s⁻¹)	电子组件位置	损伤
	材料	尺寸/mm	速度/(km·s⁻¹)	电子组件位置	蜂窝板	后板	电子组件	电缆网组件
1	PTFE/Al/Cu	$ \varnothing$7×7	3.06	蜂窝板背面	穿孔	凹陷	穿孔+烧蚀	烧蚀
2	PTFE/Al/Cu	$\varnothing $7×7	3.13	侧面板	穿孔	凹陷	烧蚀	断裂+烧蚀
3	PTFE/Al/Cu	$\varnothing $7×7	3.10	后板正面	穿孔	凹陷	穿孔+烧蚀	断裂+烧蚀

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表 2 Al2024和Al5052的主要材料参数^{[3, 30]}

Table 2. Main material parameters of Al2024 and Al5052^{[3, 30]}

材料	ρ/(g·cm⁻³)	G₀/GPa	Y₀/MPa	Y_max/MPa	β	n	γ₀	C₁/(km·s⁻¹)	S₁	c_V/(J·kg⁻¹·K⁻¹)
Al2024	2.78	28.6	260	760	310	0.185	2.18	5.328	1.338	863
Al5052	2.68	27.6	290	680	125	0.1	1.97	5.240	1.34	875

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表 3 PTFE/Al/Cu的主要材料参数^[3]

Table 3. Main material parameters of PTFE/Al/Cu^[3]

$ \rho $/(g$ \cdot $cm⁻³)	A/MPa	B/MPa	n	I/μs⁻¹	b	c	d	y
2.7	61.3	128.1	0.574	44	0.22	0.222	0.666	1.6

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表 4 数值模拟和实验2结果的对比

Table 4. Comparison of numerical simulation and Exp. 2 results

夹芯板入射孔径			夹芯板出射孔径
实验2/mm	模拟/mm	误差/%	实验2/mm	模拟/mm	误差/%
10.1	10.8	6.7	66.5	62.4	6.1

碎片云膨胀速度			碎片云头部速度
实验2/(km·s⁻¹)	模拟/(km·s⁻¹)	误差/%	实验2/(km·s⁻¹)	模拟/(km·s⁻¹)	误差/%
1.61	1.68	4.3	2.53	2.76	9.1

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