泡沫增强复合材料点阵夹芯梁抗冲击性能

王春国; 文安松; 范子豪; 黄威

doi:10.11858/gywlxb.20210807

泡沫增强复合材料点阵夹芯梁抗冲击性能

doi: 10.11858/gywlxb.20210807

王春国^1,,
文安松²,
范子豪²,
黄威^2,*, ,

1.
中国船舶重工集团公司第七一九研究所，湖北武汉　430064
2.
华中科技大学船舶与海洋工程学院，湖北武汉　430074

基金项目: 国家自然科学基金（11802100）

详细信息

作者简介:
王春国（1978－），男，硕士，主要从事船舶与海洋工程结构物研究. E-mail：wangcg@gmail.com

通讯作者:
黄　威（1987－），男，博士，讲师，主要从事冲击动力学研究. E-mail：weihuang@hust.edu.cn

中图分类号: O347
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出版历程
- 收稿日期: 2021-06-04
- 修回日期: 2021-06-18

Dynamic Failure of Foam-Reinforce Composite Lattice Sandwich Beam to Local Impulsive Load

WANG Chunguo^1
,,
WEN Ansong²,
FAN Zihao²,
HUANG Wei^{2,*
, ,}

1.
The 719 Research Institute of CSIS, Wuhan 430064, Hubei, China
2.
School of Naval Architecture and Ocean Engineering, Huazhong University of Science and Technology, Wuhan 430074, Hubei, China

摘要

摘要: 基于考虑分层失效和渐进损伤的三维Hashin失效准则，对复合材料点阵夹芯梁结构及其泡沫增强夹芯结构开展了局部冲击加载下的数值模拟分析，研究了冲击强度及泡沫增强效应对复合材料点阵夹芯梁结构抗冲击性能的影响。通过与实验的对比分析，验证了数值模型的有效性。结果显示，冲击强度的变化对结构的动态响应、失效模式及能量耗散形式都有明显的影响。泡沫增强效应使结构的横向变形响应速度降低，并且随着冲击强度的增加尤为敏感。泡沫芯材的压缩和开裂失效使得结构保持良好的完整性和更低的损伤程度，有效地降低了其他组分的能量吸收比，表明泡沫填充有效地提升了复合材料点阵梁结构在局部冲击载荷作用下的防护效能。
- 复合材料 /
- 点阵夹芯梁 /
- 抗冲击性能
Abstract: Based on the Hashin 3D failure criteria, both stiffness degradation and interface delamination are adopted to model the damage evolution of the composites, a numerical study on the composite lattice sandwich and its foam-reinforce sandwich beams subjected to local impulsive load is performed to identify the effects of impulsive intensity and foam reinforcement on the dynamic response, failure modes, and energy absorption mechanisms. The numerical result is confirmed to have a great agreement with the previously experimental results. The results show the impact strength has a significant influence on the dynamic response, failure mode, and energy dissipation mechanisms of the beams. With the reinforcement of the foam, the composite sandwich beam undergoes a slower deformed response than the lattice sandwich beam, especially for the intensive loads. The compression and cracking of the foam core reduces the degree of failure and keeps the structural integrity, and at the same time effectively decreases the energy absorption ratio of other components, indicating a noticeable improvement of impact resistance of the foam-reinforce composite lattice sandwich beam to concentrated impact load.
- composite material /
- lattice sandwich beam /
- impulsive resistance

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图 1 冲击加载实验装置和复合材料点阵结构及其单胞尺寸

Figure 1. Sketch of the experimental setup and dimensions of the lattice cell

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图 2 泡沫弹冲击加载有限元模型

Figure 2. Numerical model of the aluminum foam impact test

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图 3 复合材料点阵夹芯结构动态变形实验与模拟结果对比（v₀ = 140.8 m/s）

Figure 3. Comparison of dynamic deformation of the experiment and simulation of the composite lattice sandwich beam (v₀ = 140.8 m/s)

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图 4 泡沫增强复合材料点阵夹芯结构动态变形实验与模拟结果对比（v₀ = 139.2 m/s）

Figure 4. Comparison of dynamic deformation of the experiment and simulation of the foam reinforced composite lattice sandwich beam (v₀ = 139.2 m/s)

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图 5 背板中点动态变形对比

Figure 5. Comparison of midspan dynamic deformation between the experiment and simulation

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图 6 低速冲击下复合材料点阵夹芯梁的失效模式对比

Figure 6. Comparison of failure modes of the composite lattice sandwich beam under low-veloctiy impact

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图 7 高速冲击下复合材料点阵夹芯梁的失效模式对比

Figure 7. Comparison of failure modes of the composite lattice sandwich beam under high-veloctiy impact

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图 8 复合材料夹芯结构梁在不同冲击强度下各组分的吸能比

Figure 8. Energy absorption of different components of the composite lattice sandwich beam under different impact conditions

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表 1 T700碳纤维/环氧单向预浸料的材料属性

Table 1. Material properties of T700 carbon/epoxy prepregs

E₁₁/MPa	E₂₂/MPa	E₃₃/MPa	ν₁₂	ν₁₃	ν₂₃	G₁₂/MPa
100	8	8	0.21	0.21	0.30	4

G₁₃/MPa	G₂₃/MPa	X_t/MPa	X_c/MPa	Y_t/MPa	Y_c/MPa	Z_t/MPa
4	3	2100	700	42	160	42

Z_c/MPa	S₁₂/MPa	S₁₃/MPa	S₂₃/MPa	$\,\rho $/(kg·m^–³)
160	104	104	86	1500

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表 2 撞击初始条件及无量纲冲击强度

Table 2. Initial conditions and non-dimensional impulse of the impacts

Sample	Exp. No.	m_p/g	v₀/(m·s^–¹)	$ \overline I $	Sample	Exp. No.	m_p/g	v₀/(m·s^–¹)	$ \overline I $
Lattice sandwich	LS-1	29.8	50.6	0.25	Lattice/foam sandwich	LS/F-1	30.3	52.2	0.26
	LS-2	28.8	77.5	0.36		LS/F-2	29.1	80.5	0.38
	LS-3	29.7	140.8	0.68		LS/F-3	29.2	139.2	0.66
	LS-4	27.9	175.4	0.80		LS/F-4	30.6	167.6	0.83
	LS-5	29.9	204.1	0.99		LS/F-5	28.9	209.4	0.99

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