三维针刺复合材料参数化建模及力学性能仿真

陈国耀; 黄丰; 杨振宇; 卢子兴; 王浩然

doi:10.13801/j.cnki.fhclxb.20220725.002

三维针刺复合材料参数化建模及力学性能仿真

doi: 10.13801/j.cnki.fhclxb.20220725.002

1.
北京航空航天大学　航空科学与工程学院，北京 100083
2.
中国航天科工集团第六研究院四十一所，呼和浩特 010010

基金项目: 国家自然科学基金(11972057；11972058)；国家科技重大专项(2017-VII-0003-0096)

详细信息

通讯作者:
杨振宇，博士，副教授，博士生导师，研究方向为复合材料力学　E-mail: zyyang@buaa.edu.cn

中图分类号: TB330.1
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出版历程
- 收稿日期: 2022-03-21
- 修回日期: 2022-07-14
- 录用日期: 2022-07-14
- 网络出版日期: 2022-07-25
- 刊出日期: 2022-08-22

Parametric modeling and mechanical properties simulation of three-dimensional needling composites

1.
School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China
2.
The 41^st Institute of the Sixth Academy of China Aerospace Science & Industry Corp., Huhhot 010010, China

Funds: National Natural Science Foundation (11972057; 11972058); National Science and Technology Major Project(2017-VII-0003-0096)

摘要

摘要: 提出了一套三维针刺复合材料建模方法，并应用于针刺碳/酚醛复合材料的力学性能仿真分析。首先基于虚拟纤维技术，采用商用有限元软件ABAQUS，实现了叠层材料针刺工艺过程的数值模拟，获得了针刺区域附近的纤维丝在针刺过程中的变形规律，据此建立了受针刺影响区域内的纤维取向、损伤百分比与针刺工艺参数之间的关系；将这一关系引入到针刺复合材料代表性体积单元(RVE)模型中，较准确地体现真实材料中针刺区结构特征。利用此模型对材料的弹性性能、强度进行预测，结果与实验值吻合良好，验证了模型的有效性；在此基础上，进一步讨论了针刺密度、针刺深度等参数对复合材料力学性能的影响规律。本文的研究结果对针刺复合材料的力学分析与优化设计具有一定的指导意义。
- 三维针刺复合材料 /
- 有限元 /
- 虚拟纤维 /
- 弹性性能 /
- 强度
Abstract: The mechanical properties of needling carbon/phenolic composites were simulated and described along with a general finite element modeling (FEM) approach for 3D needling composites. First, the numerical simulation of the needling process of laminated materials was accomplished using virtual fiber technology with the commercial FEM program ABAQUS, and the deformation of the fiber near the needling area in the formation process was simulated. Based on this, a correlation between fiber orientation, damage rate, and needling parameters was found in the needling process-affected area. This relationship was then introduced into the representative volume element (RVE) of needling composites, which can accurately reflect the structural characteristics of real materials. This model was used to predict the stiffness and strength of materials, and the results are in good agreement with the experimental values, which verifies the validity of the model. Based on this, the effects of needling parameters, such as needling density and needing depth, on mechanical properties of composites were discussed. The results of this study are expected to contribute to the mechanical analysis and optimal design of needling composites.
- 3D needling composites /
- finite element /
- virtual fiber /
- elastic properties /
- strength

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图 1 三维针刺碳/酚醛复合材料的铺层材料及针刺过程：(a) 缎纹布与网胎铺层；(b) 针刺板结构

Figure 1. Schematic of plies and needling process of 3D needled carbon/phenolic composites: (a) Satin and net layer plies; (b) Structure of needle plate

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图 2 针刺碳/酚醛复合材料微观形貌(橘红色实线为针刺位置，黑色虚线为变形区，红色虚线为碳布)

Figure 2. Microstructure of needled carbon/phenolic composites (Orange lines for the needling region, black dashed lines for the deformed region, and yellow dashed lines for the carbon cloth)

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图 3 单轴拉伸试件

Figure 3. Specimen for uniaxial tensile test

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图 4 随机纤维的空间位置关系定义

Figure 4. Definition of spatial position of two random fibers

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图 5 网胎层的随机纤维网络模型

Figure 5. Random fibers network model of the net layer

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图 6 网胎层针刺模拟中针刺深度为5 mm时模拟结果

Figure 6. Net layer needling simulation results with needling depth of 5 mm

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图 7 网胎层针刺模拟中不同针刺深度下位移随针刺中心距离的关系

Figure 7. Relationship between the displacement and the distance to needling center at different needling depth of net layer needling simulation

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图 8 缎纹布的虚拟纤维模型

Figure 8. Virtual fiber model of satin fabric

a—Length of major axis of the yarn’s cross section; b—Length of minor axis of the yarn’s cross section; l—Spacing between the adjacent yarns

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图 9 碳布层针刺模拟的典型针刺位置

Figure 9. Typical needling positions on the satin plies for simualtions

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图 10 碳布层针刺模拟过程中：(a) 刺针上的载荷与刺入深度的关系；(b) 针刺过程中纤维断裂

Figure 10. Satin fabric needling simulation: (a) Relationship between the reaction force on the needle and the penetration depth; (b) Fiber breakage in the needling process

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图 11 三维针刺碳/酚醛复合材料的第一层表面针迹

Figure 11. Needling trail in first ply of 3D needled carbon/phenolic composites

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图 12 三维针刺碳/酚醛复合材料的体素化针刺代表性体积单元(RVE)及单元位置关系

Figure 12. 3D needled carbon/phenolic composites' Voxelized needling representative volume element (RVE) and location of elements

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图 13 体素化针刺单元(VNC)模型中处于Case 3范围内的单元及材料方向

Figure 13. Elements located in Case 3 and its local material direction in the voxelized needling cell (VNC) model composites

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图 14 三维针刺碳/酚醛复合材料的体素化针刺RVE模型

Figure 14. Voxelized needling RVE model of 3D needled carbon/phenolic composites

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图 15 三维针刺碳/酚醛复合材料单轴拉伸的数值模拟结果和试验结果的对比

Figure 15. Comparison between numerical simulation and test results of 3D needled carbon/phenolic composites' uniaxial tension

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图 16 三维针刺碳/酚醛复合材料单轴拉伸的弹性阶段应力云图

Figure 16. Stress contour plot in elastic deformation of 3D needled carbon/phenolic composites' uniaxial tension

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图 17 拉伸应变$ {\varepsilon _x} $=0.11%时网胎层损伤情况

Figure 17. Damage of net layer at tensile strain ${\varepsilon _x}$=0.11%

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图 18 拉伸应变${\varepsilon _x}$=0.24%时针刺纤维束 (a) 及缎布 (b) 损伤情况

Figure 18. Damage of needled fiber bundles (a) and satin plies (b) at tensile strain ${\varepsilon _x}$=0.24%

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图 19 三维针刺碳/酚醛复合材料的VNC模拟结果与文献结果对比

Figure 19. Comparison of VNC simulation with the results from previous references of 3D needled carbon/phenolic composites

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图 20 三维针刺碳/酚醛复合材料的归一化弹性性能随针刺深度的变化曲线

Figure 20. Relationship between the normalized elastic properties and the needling depth of 3D needled carbon/phenolic composites

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图 21 三维针刺碳/酚醛复合材料的弹性性能随针刺密度的变化曲线

Figure 21. Relationship between the normalized elastic properties and the needling density of 3D needled carbon/phenolic composites

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图 22 不同针刺深度下三维针刺碳/酚醛复合材料的单轴拉伸的应力-应变曲线

Figure 22. Stress-strain curves of uniaxial tension under different needling depth of 3D needled carbon/phenolic composites

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图 23 不同针刺密度下三维针刺碳/酚醛复合材料的单轴拉伸的应力-应变曲线

Figure 23. Stress-strain curves of uniaxial tension under different needling density of 3D needled carbon/phenolic composites

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表 1 碳布层不同针刺深度下纤维断裂百分比

Table 1. Percentage of fiber breakage with different needling depth of satin fabric layer

H_d/mm	4	6	8
Case 1	0.00%	0.00%	0.22%
Case 2	1.10%	2.87%	4.08%
Case 3	2.65%	5.74%	11.37%

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表 2 纤维和基体的力学性能参数

Table 2. Mechanical properties of fiber and matrix

Material		${E_{11}}$/GPa	${E_{22}}$/GPa	${G_{12}}$/GPa	${G_{23}}$/GPa	${\nu _{12}}$	${\nu _{23}}$
T800^[22]	Fiber	195.00	8.58	4.60	2.9	0.33	0.48
Phenolic resin^[23]	Matrix	4.10	—	1.52	—	0.35	—
Notes: ${E_{11}}$, ${E_{22}}$—Young’s modulus; ${G_{12}}$, ${G_{23}}$—Shear modulus; ${v_{12}}$, ${v_{23}}$—Poisson’s ratio.

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表 3 不同针刺深度下缎纹布弹性性能

Table 3. Elastic properties of satin fabric at different needling depths

${H_{\text{d}}}$/mm	${E_{11}}$/GPa	${E_{33}}$/GPa	${G_{12}}$/GPa	${G_{13}}$/GPa	${\nu _{12}}$	${\nu _{23}}$
0	34.07	6.97	2.40	2.17	0.103	0.100
4	33.83	6.96	2.40	2.16	0.100	0.100
6	32.52	6.87	2.35	2.14	0.103	0.103
8	30.99	6.75	2.30	2.11	0.103	0.105
Notes: E₃₃—Young’s modulus; G₁₃—Shear modulus.

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表 4 三维针刺碳/酚醛复合材料不同铺层的布针形式

Table 4. Needling form in different plies of 3D needled carbon/phenolic composites

Needling step	First ply	Second ply	Third ply
First needling along X direction	(0, 0)	(0, 5)	(0, 10)
First needling along Y direction	(0, 3)	(5, 3)	(10, 3)
Second needling along X direction	(0, 2.5)	(0, 7.5)	(0, 12.5)
Second needling along Y direction	(2.5, 3)	(7.5, 3)	(12.5, 3)

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表 5 石墨基体力学性能^[14]

Table 5. Mechanical properties of graphite matrix^[14]

${E_{\text{m}}}$/GPa	${v_{\text{m}}}$	$R_{\text{m}}^{\text{t}}$/MPa	$R_{\text{m}}^{\text{c}}$/MPa	$R_{\text{m}}^{\text{s}}$/MPa
9.235	0.23	14.7	67.8	19.1
Notes: $ {E}_{\mathrm{m}},{\nu }_{\mathrm{m}} $—Young’s modulus and Poisson's ratio; $ {R}_{\mathrm{m}}^{\mathrm{t}},\;{R}_{\mathrm{m}}^{\mathrm{c}},\;{R}_{\mathrm{m}}^{\mathrm{s}} $—Tensile strength, compressive strength and shear strength, respectively.

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表 6 三维针刺碳/酚醛复合材料弹性性能计算结果对比

Table 6. Comparison of the elastic properties of 3D needled carbon/phenolic composites

	${E_{11}}$/GPa	${G_{12}}$/GPa	${v_{12}}$
VNC	47.42	12.48	0.12
FEM^[24]	57.35	14.69	0.12
Experiment^[24]	50.17	12.99	0.12
Notes: VNC—Voxelized needling cell; FEM—Finite element method.

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