铝球微气囊超结构Whipple屏抗超高速冲击性能物质点法分析

毛志超; 于成; 李晓杰; 王小红; 闫鸿浩; 王宇新

doi:10.11883/bzycj-2024-0265

铝球微气囊超结构Whipple屏抗超高速冲击性能物质点法分析

doi: 10.11883/bzycj-2024-0265

大连理工大学力学与航空航天学院, 辽宁大连 116024

详细信息

作者简介:
毛志超（2000－　），男，硕士研究生，mzc@mail.dlut.edu.cn

通讯作者:
王宇新（1972－　），男，博士，副教授，wyxphd@dlut.edu.cn

中图分类号: O389; V414.8
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- 文章访问数: 167
- HTML全文浏览量: 35
- PDF下载量: 62
- 被引次数: 0
出版历程
- 收稿日期: 2024-08-11
- 修回日期: 2025-04-21
- 网络出版日期: 2025-04-24
- 刊出日期: 2025-07-05

A study on hypervelocity impact resistance of the Whipple shield with aluminum spherical micro-airbag metastructure using material point method

School of Mechanics and Aerospace Engineering, Dalian University of Technology, Dalian 116024, Liaoning, China

摘要

摘要: 为了提升Whipple屏对太空碎片的超高速冲击防护性能，在不增加多孔材料、碳纤维等其他吸能材料的前提下，设计了一种铝球微气囊阵列超结构，并应用3D打印技术进行加工制备。同时，构建了初速度为7.5 km/s的球形弹丸冲击靶板的计算模型，用以研究超高速冲击防护性能；将物质点法的计算精度与实验进行对比验证后，开展了超高速冲击Whipple屏三维数值模拟；通过与单层铝板的超高速冲击模拟得到的靶板穿孔尺寸、碎片云形貌及其速度、动量、能量和温度等参数比较分析，讨论并揭示了铝球微气囊超结构的能量吸收与耗散机理。结果表明：铝球微气囊超结构Whipple屏对弹丸轴向动能的削减值比单层铝板提高了300 J，其碎片云径向最大膨胀半径比单层铝板增大了32.2 mm。由此可知，铝球微气囊超结构Whipple屏可以显著提高对空间碎片超高速冲击的防护性能。同时，与相关实验数据对比结果表明，物质点法超高速冲击数值模拟具有较高的计算精度，可以作为研究开发新型Whipple屏的数值实验工具。
- 物质点法 /
- 超高速冲击 /
- Whipple防护屏 /
- 超结构 /
- 空间碎片
Abstract: To enhance the hypervelocity impact protection performance of Whipple shields against high-speed space debris, an aluminum spherical micro-airbag array metastructure was designed without incorporating additional energy-absorbing materials such as porous materials or carbon fibers. This metastructure was fabricated using 3D printing technology. The protective performance of the Whipple shield was investigated and analyzed by constructing a numerical model of a spherical projectile with an initial velocity of 7.5 km/s impacting both the single-layer aluminum plate and the aluminum spherical micro-airbag metastructure. The finite element method is often inadequate for accurately calculating large plastic deformations and fracture damage problems, particularly when mesh distortions are involved. Therefore, the material point method (MPM) was employed in this study to simulate hypervelocity impact scenarios. After verifying the reliability of the MPM calculations through experiments, a three-dimensional numerical simulation of hypervelocity impacts on the Whipple shield was conducted. The mechanism of energy absorption and dissipation by the aluminum spherical micro-airbag metastructure was elucidated through a comparative analysis of the perforation size, debris cloud morphology, and key parameters such as velocity, momentum, energy, and temperature with those of a single-layer aluminum plate subjected to hypervelocity impact. The results indicate that the Whipple shield with the aluminum spherical micro-airbag metastructure reduces the axial kinetic energy of the projectile by 300 J more than the single-layer aluminum plate. In addition, the maximum expansion radius of the debris cloud is 32.2 mm larger than that of the single-layer aluminum plate. These findings demonstrate that the Whipple shield with the aluminum spherical micro-airbag metastructure significantly enhances protection against hypervelocity impacts from space debris. Moreover, when compared with relevant experimental data, the material point method simulation proves to be an effective computational tool for researching and developing new types of Whipple shields.
- material point method /
- hypervelocity impact /
- Whipple shield /
- metastructure /
- space debris

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图 1 Whipple屏结构示意图

Figure 1. Schematic diagram of the Whipple shield

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图 2 铝球微气囊超结构Whipple屏示意图

Figure 2. Schematic diagram of aluminum spherical micro-airbag metastructure Whipple shield

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图 3 三维模型结构

Figure 3. Three-dimensional modeling structure

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图 4 3D打印实物照片

Figure 4. Picture of 3D printed physical model

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图 5 单层铝板Whipple屏超高速冲击模型

Figure 5. Single-layer aluminum plate Whipple shield hypervelocity impact model

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图 6 2种不同速度弹丸高速冲击铝板模拟

Figure 6. Simulation of high-speed impact of projectiles with two different velocities on aluminum plates

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图 7 实验与数值模拟的对比

Figure 7. Comparison of experimental and simulation results

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图 8 铝球微气囊超结构Whipple防护屏屏超高速冲击模型

Figure 8. Hypervelocity impact model of the Whipple shield with aluminum spherical micro-airbag metastructure

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图 9 铝球微气囊超结构Whipple屏碎片云形貌

Figure 9. Morphology of the debris cloud for the Whipple shield with aluminum spherical micro-airbag metastructure

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图 10 铝球微气囊超结构Whipple屏碎片云等效塑性应变

Figure 10. Effective plastic strain of debris cloud for the Whipple shield with aluminum spherical micro-airbag metastructure

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图 11 单层铝板Whipple屏超高速冲击模型

Figure 11. Hypervelocity impact model for single-layer aluminum plate Whipple shield

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图 12 碎片云形貌

Figure 12. Morphology of debris cloud

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图 13 碎片云的结构示意图

Figure 13. Schematic diagram of debris cloud structure

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图 14 t=20.0 μs碎片云形貌的对比

Figure 14. Comparison of debris cloud morphology at t=20.0 μs

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图 15 Whipple屏面板穿孔形貌

Figure 15. Perforation morphology for faceplate of the Whipple shield

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图 16 2种Whipple屏的弹丸轴向平均速度

Figure 16. Axial average residual velocity of the projectiles for the two Whipple shields

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图 17 单层铝板Whipple屏各组件的动能

Figure 17. Kinetic energy for each component of the Whipple shield with single-layer aluminum plate

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图 18 铝球微气囊超结构Whipple屏各组件的动能

Figure 18. Kinetic energy for each component of the Whipple shield with aluminum spherical micro-airbag metastructure

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图 19 弹丸在x方向的动能

Figure 19. Kinetic energy of the projectile in x-direction

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图 20 弹丸在y方向的动能

Figure 20. Kinetic energy of the projectile in y-direction

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图 21 弹丸在z方向的动能

Figure 21. Kinetic energy of the projectile in z-direction

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图 22 Whipple屏冲击温度计算云图

Figure 22. Impact temperature contours of the two Whipple shields

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表 1 Al2017和2Al2的Steinberg-Guinan模型参数

Table 1. Steinberg-Guinan model parameters for Al2017 and 2Al2

材料	$ E / \mathrm{G}\mathrm{P}\mathrm{a}$	$ \rho / (\mathrm{k}\mathrm{g}\cdot {\mathrm{m}}^{-3})$	$ \beta $	$ {Y}_{0} / \mathrm{M}\mathrm{P}\mathrm{a}$	$ {Y}_{\mathrm{m}\mathrm{a}\mathrm{x}}/ \mathrm{M}\mathrm{P}\mathrm{a} $	$ n $	$ {G}'_{p} $	$ {G}'_{T}/( \mathrm{M}\mathrm{P}\mathrm{a}\cdot {\mathrm{K}}^{-1}) $	$ {Y}'_{p}$	$ {c}_{V} / (\mathrm{J}\cdot {\mathrm{k}\mathrm{g}}^{-1}\cdot {\mathrm{K}}^{-1}) $
Al2017	71.8	2 790	300	270	506	0.150	1.740	−16.00	0.016 7	900
2Al2	76.0	2 785	310	260	760	0.185	1.865	−17.62	0.017 0	863

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表 2 Al2017和2Al2的Mie-Grüneisen状态方程参数

Table 2. Mie-Grüneisen equation of state parameters for Al2017 and 2Al2

材料	$ {c}_{\mathrm{g}}/(\mathrm{m}\cdot{\mathrm{s}}^{-1}) $	S₁	S₂	S₃	γ₀
Al2017	5 370	1.290	0	0	2.0
2Al2	5 328	1.338	0	0	2.0

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表 3 实验与物质点法模拟得到的铝板穿孔直径的对比

Table 3. Comparison between experimental and MPM simulation perforation diameters of the aluminum plate

序号	弹丸直径/mm	弹丸速度/(km·s⁻¹)	实验穿孔直径/mm	物质点法模拟穿孔直径/mm	相对误差/%
1	3.96	4.81	7.36	7.20	2.2
2	4.23	4.46	7.10	7.20	1.4
3	4.89	4.03	7.82	7.80	0.2
4	4.98	5.00	8.38	8.20	2.1
5	5.56	4.10	8.68	9.20	6.0

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表 4 Al6061-T6和A2024-T4的Steinberg-Guinan模型参数^[41]

Table 4. Steinberg-Guinan constitutive model parameters for Al6061-T6 and A2024-T4^[41]

材料	$ E / \mathrm{G}\mathrm{P}\mathrm{a}$	$ \rho / (\mathrm{k}\mathrm{g}\cdot {\mathrm{m}}^{-3})$	$ \beta $	$ {Y}_{0}/ \mathrm{M}\mathrm{P}\mathrm{a} $	$ {Y}_{\rm{max}} /\mathrm{M}\mathrm{P}\mathrm{a}$	$ n $	$ {G}'_{p}$	$ {G}'_{T} / (\mathrm{M}\mathrm{P}\mathrm{a}\cdot {\mathrm{K}}^{-1}) $	$ {Y}'_{p} $	$ {c}_{V}/ (\mathrm{J}\cdot {\mathrm{k}\mathrm{g}}^{-1}{\cdot \mathrm{K}}^{-1}) $
Al6061-T6	73.4	2 703	125	290	680	0.100	1.800	–17.00	0.018 9	885
Al2024-T4	76.0	2 785	310	260	760	0.185	1.865	−17.62	0.017 0	863

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表 5 Al6061-T6和Al2024-T4材料Mie-Grüneisen状态方程参数^[41]

Table 5. Mie-Grüneisen equation of state parameters for Al6061-T6 and Al2024-T4^[41]

材料	c_g/(m·s⁻¹)	S₁	S₂	S₃	γ₀
Al6061-T6	5 240	1.400	0	0	1.97
Al2024-T4	5 328	1.338	0	0	2.00

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表 6 主体碎片云膨胀尺寸

Table 6. Expansion size of the outer bubble debris clouds

Whipple屏类型	D_a/mm	D_b/mm	D_c/mm
单层铝板	96.0	67.2	65.8
铝球微气囊超结构	77.2	99.4	85.8

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表 7 2种Whipple屏穿孔尺寸

Table 7. Perforation sizes of the two Whipple shields

类型	a/mm	b/mm
铝球微气囊超结构Whipple屏面板	28.4	29.2
单层铝板Whipple屏面板	45.6	44.4
铝球微气囊超结构Whipple屏背板	57.6	64.8
单层铝板Whipple屏面背板	46.0	46.0

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