碳纳米管/碳纤维增强复合材料层合板低速冲击响应和破坏的数值模拟

王敏; 文鹤鸣

doi:10.11883/bzycj-2021-0050

碳纳米管/碳纤维增强复合材料层合板低速冲击响应和破坏的数值模拟

doi: 10.11883/bzycj-2021-0050

王敏,
文鹤鸣^,

中国科学技术大学中国科学院材料力学行为和设计重点实验室，安徽合肥 230026

详细信息

作者简介:
王　敏（1996－　），女，硕士研究生，wangmin9@mail.ustc.edu.cn

通讯作者:
文鹤鸣（1965－　），男，博士，教授，博士生导师，hmwen@ustc.edu.cn

中图分类号: O347.3
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- 被引次数: 11
出版历程
- 收稿日期: 2021-02-02
- 修回日期: 2021-05-06
- 网络出版日期: 2022-03-08
- 刊出日期: 2022-04-07

Numerical simulations of response and failure of carbon nanotube/carbon fibre reinforced plastic laminates under impact loading

WANG Min,
WEN Heming^,

CAS Key Laboratory for Mechanical Behavior and Design of Materials, University of Science and Technology of China, Hefei 230026, Anhui, China

摘要

摘要: 碳纳米管/碳纤维增强复合材料（carbon nanotube/carbon fibre reinforced plastic，CNT/CFRP）是一种多尺度复合材料，比传统CFRP有更好的综合性能和更广阔的应用前景。对CNT/CFRP在低速冲击下的响应和破坏进行了数值模拟研究。首先，基于先前的研究通过引入基体增韧因子、残余强度因子并改进损伤耦合方程，建立了新的FRP动态渐进损伤模型；然后，利用新建立的本构模型并结合黏结层损伤模型，对4种碳纳米管含量的增韧碳纤维增强树脂基复合材料层合板在5个能量下的冲击实验进行了数值模拟；最后，将模拟结果与文献中的相关实验结果进行了比较，并讨论了冲击速度的影响。结果表明：新建立的FRP本构模型能够预测CNT/CFRP层合板在低速冲击载荷作用下的响应、破坏过程和分层形貌，模拟得到的载荷-位移曲线和破坏形貌与实验吻合较好；冲击速度会影响CNT/CFRP层合板拉伸和压缩破坏的比例，相同的冲击能量下，更大的冲击速度会造成更多的拉伸破坏。
- 碳纤维增强复合材料层 /
- 碳纳米管 /
- 动态渐进损伤模型 /
- 黏结单元模型 /
- 基体增韧因子 /
- 残余强度因子 /
- 损伤耦合 /
- 冲击载荷
Abstract: Fibre reinforced plastic (FRP) laminates have been widely used in various engineerings due to their excellent mechanical properties. However, FRP laminates may be subjected to impact loading and delamination is one of the major concerns which is caused by the poor performance of matrix and the poor bonding between fibre and matrix. To improve the bonding strength, some toughening technologies have been developed including the modification of matrix by adding nano fillers such as carbon nanotubes. In this paper, numerical simulations of the response and failure of carbon nanotube/carbon fibre reinforced plastic (CNT/CFRP) under low velocity impact loading were performed. Firstly, on the basis of the previous work, a new dynamic progressive damage model for FRP laminates was developed by introducing a matrix toughening factor and a residual strength factor into the damage criterion and damage evolution equation respectively, together with an improved damage coupling equation which was changed from the original sum form to product form. The new dynamic progressive damage model was used to describe the intralaminar damage, and a cohesive element model to describe the interlaminar damage of the CNT/CFRP laminates. Both models were incorporated into the ABAQUS/Explicit finite element program by the user-defined material subroutine VUMAT. Then, numerical simulation was conducted for the response and failure of CNT/CFRP composites subjected to low velocity impact loading. Finally, the numerical results were compared with some available experimental data and the influence of impact velocity was discussed. It transpires that the results predicted from the present model are found to be in good agreement with the test data for CNT/CFRP laminates in terms of load-displacement curve and failure pattern, and the delamination damage at the interlaminar interface decreases gradually with increasing CNT content. It also transpires that the impact velocity affects the ratio of compression and tensile failure of FRP laminates, and under the same impact energy, a larger impact velocity will cause more tensile failure.
- carbon fiber reinforced plastics (CFRP) /
- carbon nanotube /
- dynamic progressive damage model /
- cohesive element model /
- matrix toughening factor /
- residual intensity factor /
- damage coupling /
- impact loading

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图 1 损伤演化示意图

Figure 1. Schematic diagrams of damage evolution

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图 2 冲击载荷下 CFRP 层合板的有限元模型

Figure 2. Finite element model for CFRP laminates under impact loading

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图 3 CNT含量对CNT/FRP层间剪切强度的影响

Figure 3. Effect of CNT content on the intelaminar shear strength

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图 4 不同CNT含量黏结层模型的牵引力-位移关系

Figure 4. The traction-separation law in the cohesive element model with different CNT contents

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图 5 数值模拟的载荷-位移曲线与实验^[11]的比较

Figure 5. Comparison of the force-displacement curves between numerical simulation and experiment^[11]

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图 6 数值模拟的破坏形貌与实验^[11]的比较

Figure 6. Comparison of the damage morphologies between numerical simulation and experiment^[11]

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图 7 数值模拟的破坏历程

Figure 7. Damage histories obtained by numerical simulations

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图 8 冲击能量为15 J时不同MWCNTs含量CFRP层合板的分层形貌

Figure 8. Delaminations of CFRP laminatses with different MWCNTs content under the impact energy of 15 J

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图 9 冲击能量为120 J时不同MWCNTs含量CFRP层合板的分层形貌

Figure 9. Delaminations of CFRP laminates with different MWCNTs content under the impact energy of 120 J

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图 10 冲击能量为120 J时不同冲击速度对CNT/CFRP冲击载荷-位移曲线的影响

Figure 10. Effect of impact velocity on the impact load-displacement curve for CNT/CFRP under the impact energy of 120 J

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图 11 冲击能量为120 J时下不同冲击速度对CNT/CFRP损伤的影响

Figure 11. Effect of impact velocity on the damage of CNT/CFRP under the impact energy of 120 J

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表 1 等效位移和等效应力

Table 1. Equivalent displacement and equivalent stress

j	损伤模式	δ_eq,j	σ_eq,j
1	x方向的纤维拉/剪损伤	${L_{\text{c}}}\sqrt {{{\left\langle {{\varepsilon _x}} \right\rangle }^2} + \gamma _{x{\textit{z}}}^2}$	$\left. {L_{\text{c}}}\left( {{E_x}{{\left\langle {{\varepsilon _x}} \right\rangle }^2} + {G_{x{\textit{z}}}}\gamma _{x{\textit{z}}}^2} \right)\right/{\delta _{{\text{eq,1}}}}$
2	y方向的纤维拉/剪损伤	${L_{\text{c}}}\sqrt {{{\left\langle {{\varepsilon _y}} \right\rangle }^2} + \gamma _{y{\textit{z}}}^2}$	$\left. {L_{\text{c}}}\left( {{E_y}{{\left\langle {{\varepsilon _y}} \right\rangle }^2} + {G_{y{\textit{z}}}}\gamma _{y{\textit{z}}}^2} \right)\right/{\delta _{{\text{eq,2}}}}$
3	x方向的纤维压缩损伤	${L_{\text{c}}}\left\langle {{\varepsilon '_x}} \right\rangle$	${E_x}\left\langle {{\varepsilon '_x}} \right\rangle$
4	y方向的纤维压缩损伤	${L_{\text{c}}}\left\langle {{\varepsilon '_y}} \right\rangle$	${E_y}\left\langle {{\varepsilon '_y}} \right\rangle$
5	厚度方向的纤维压溃	${L_{\text{c}}}\left\langle { - {\varepsilon _{\textit{z}}}} \right\rangle$	${E_{\textit{z}}}\left\langle { - {\varepsilon _{\textit{z}}}} \right\rangle$
6	面内的基体剪切损伤	${L_{\text{c}}}\sqrt {\gamma _{xy}^2}$	${G_{xy}}\sqrt {\gamma _{xy}^2}$
7	厚度方向的基体拉剪损伤	${L_{\text{c}}}\sqrt {{{\left\langle {{\varepsilon _{\textit{z}}}} \right\rangle }^2} + \gamma _{x{\textit{z}}}^2 + \gamma _{y{\textit{z}}}^2}$	$\left. {L_{\text{c}}}\left( {{E_{\textit{z}}}{{\left\langle {{\varepsilon _{\textit{z}}}} \right\rangle }^2} + {G_{x{\textit{z}}}}\gamma _{x{\textit{z}}}^2 + {G_{y{\textit{z}}}}\gamma _{y{\textit{z}}}^2} \right)\right/{\delta _{{\text{eq,7}}}}$

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表 2 CFRP单层板的材料参数

Table 2. Parameters for CFRP laminate

${E_x}$ /GPa	${E_y}$ /GPa		${E_{\textit{z}}}$ /GPa		${\nu _{xy}}$		${\nu _{y{\textit{z}}}}$		${\nu _{x{\textit{z}}}}$		${G_{xy}}$ /GPa		${G_{y{\textit{z}}}}$ /GPa		${G_{x{\textit{z}}}}$ /GPa		${S_{{\text{t}},x}}$ , ${S_{{\text{t,}}y}}$ /MPa	${S_{{\text{c,}}x}}$ , ${S_{{\text{c,}}y}}$ /MPa
68^[12]	68^[12]		10^[12]		0.22^[12]		0.49^[12]		0.49^[12]		5.0^[12]		4.5^[12]		4.5^[12]		420	420^[13]

${S_{{\text{t,}}{\textit{z}}}}$ /MPa		${S_{{\text{c,}}{\textit{z}}}}$ /MPa		${S_{xy}}$ /MPa		${S_{y{\textit{z}}}}$ /MPa		${S_{x{\textit{z}}}}$ /MPa		${S_{{\text{sf}}}}$ /MPa		φ		$\delta _{{\text{eq,1}}}^{\text{f}}$ , $\delta _{{\text{eq,2}}}^{\text{f}}$ /mm		$\delta _{{\text{eq,3}}}^{\text{f}}$ , $\delta _{{\text{eq,4}}}^{\text{f}}$ /mm		$\delta _{{\text{eq,5}}}^{\text{f}}$ /mm
49.5^[13]		150		98^[14]		45		45		300		10		0.2		0.025^[12]		0.05^[12]

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表 3 CNT/CFRP材料参数

Table 3. Parameters for CNT/CFRP laminates

w/%	S	f_rs,j		ɛ_x,limit, ɛ_y,limit	ɛ_expn	ɛ_crsh	ɛ_distor
w/%	S	j=1~2	j=3~5	ɛ_x,limit, ɛ_y,limit	ɛ_expn	ɛ_crsh	ɛ_distor
0	1.0	0.08	0.1	2.1	3.3	0.001	2.0
0.5	0.5	0.15	0.1	2.4	5.2	0.001	5.0
1.0	0.5	0.15	0.1	2.4	5.2	0.001	5.0
1.5	0.5	0.15	0.1	2.4	5.2	0.001	5.0

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表 4 黏结层单元参数

Table 4. Parameters for cohesive elements

w/%	$t_{\rm{n}}^0$ /MPa	$t_{\rm{s}}^{{0}}$ /MPa	$t_{\rm{t}}^{{0}}$ /MPa	${G}_{{\text{Ⅰ}}{\rm{C}}}$ /（N·mm⁻¹）	${G}_{{\text{Ⅱ}}{\rm C}}$ /（N·mm⁻¹）	${G}_{{\text{Ⅲ}}{{\rm{C}}}}$ /（N·mm⁻¹）	${K_{\rm{n}}},{K_{\rm{s}}},{K_{\rm{t}}}$ /（MPa·mm⁻¹）
0	3.3^[22]	7.0^[22]	7.0^[22]	0.33^[22]	0.8^[22]	0.8^[22]	850^[22]
0.5	3.7125	7.8750	7.8750	0.41766	1.0125	1.0125	850
1.0	4.1250	8.7500	8.7500	0.51563	1.2500	1.2500	850
1.5	4.5375	9.6250	9.6250	0.62391	1.5125	1.5125	850

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