碳纤维/环氧树脂复合材料缠绕接头拉伸失效机制

郭丽君; 陆方舟; 李想; 蔡登安; 张庆茂; 陈建农; 刘伟先; 周光明

doi:10.13801/j.cnki.fhclxb.20200102.001

碳纤维/环氧树脂复合材料缠绕接头拉伸失效机制

郭丽君^1,,
陆方舟^1,,
李想^1,,
蔡登安^1,,
张庆茂^2,,
陈建农^2,,
刘伟先^2,,
周光明^1, ,

1.
南京航空航天大学　机械结构力学及控制国家重点实验室，南京 210016
2.
成都飞机设计研究所，成都 610091

基金项目: 江苏高校优势学科建设工程(PAPD)；江苏省基础研究计划(自然科学基金)(BK20190394)；中央高校基本科研业务费专项资金(NS2019001)

详细信息

通讯作者:
周光明，博士，教授，博士生导师，研究方向为先进复合材料结构设计及工程问题的计算机建模　E-mail：zhougm@nuaa.edu.cn

中图分类号: TB332
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出版历程
- 收稿日期: 2019-10-22
- 录用日期: 2019-12-12
- 网络出版日期: 2020-01-01
- 刊出日期: 2020-09-14

Tensile failure mechanism of carbon fiber/epoxy composite winding joint

1.
State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Chengdu Aircraft Design & Research Institute, Chengdu 610091, China

摘要

摘要: 通过试验及数值模拟对碳纤维/环氧树脂复合材料缠绕接头轴向拉伸失效机制进行研究。基于ABAQUS有限元软件，通过连续介质损伤模型及内聚区模型，分别对碳纤维/环氧树脂复合材料缠绕接头各部件及界面进行模拟，编写用户自定义材料子程序(UMAT)，建立复合材料的渐进损伤模型，最终得到碳纤维/环氧树脂复合材料缠绕接头的应力分布和载荷-位移曲线，并与试验结果对比确定结构的失效机制。结果表明：有限元分析所得碳纤维/环氧树脂复合材料缠绕接头损伤部位及失效模式与试验吻合，失效载荷与试验值相差较小，证明仿真分析方法的有效性。通过对比失效模式发现，拉伸载荷作用下，链环是主承力部件，其弧形端部是应力集中处，纤维断裂即从此处开始发生并向外扩展，导致链环断裂及整体结构破坏。
- 缠绕接头 /
- 复合材料 /
- 轴向拉伸 /
- 失效机制 /
- 内聚区模型
Abstract: The axial tensile failure mechanism of carbon fiber/epoxy composite winding joint was studied by means of experiment and simulation. Based on ABAQUS, the continuum damage model and cohesive zone model were used to simulate each part and interface of the carbon fiber/epoxy composite winding joint, respectively. The progressive damage model of the carbon fiber/epoxy composite was established by writing user-defined material subroutine(UMAT). As a result, the stress distribution and load-displacement curve of the carbon fiber/epoxy composite winding joint were obtained and the failure mechanism of the structure was determined by comparison with the experimental results. The results show that the calculated damage position and failure modes of the carbon fiber/epoxy composite winding joint agree well with the experimental results, and the difference between the calculated value and test value of the failure load is small, which proves the validity of the simulation analysis method. By comparing the failure modes, it is found that under tensile load, the loop plies are the main bearing component, and the curved end of which is the position where the stress is concentrated. The fiber fracture starts from here and gradually spreads outward until the loop plies fracture, which leads to the structural damage.
- winding joint /
- composite /
- axial tensile /
- failure mechanism /
- cohesive zone model

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图 1 碳纤维/环氧树脂复合材料缠绕接头几何尺寸

Figure 1. Geometry configuration of carbon fiber/epoxy composite winding joint

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图 2 复合材料缠绕接头试件加载示意图

Figure 2. Loading diagram of composite winding joint specimen

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图 3 复合材料缠绕接头试件装夹示意图

Figure 3. Clamping diagram of composite winding joint specimen

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图 4 复合材料缠绕接头应变片布置示意图

Figure 4. Schematic of strain gauge positions of composite winding joint

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图 5 碳纤维/环氧树脂复合材料缠绕接头的载荷-位移曲线

Figure 5. Load-displacement curves of carbon fiber/epoxy composite winding joint

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图 6 碳纤维/环氧树脂复合材料缠绕接头试件T-1应变-载荷曲线

Figure 6. Strain-load curves of carbon fiber/epoxy composite winding joint specimen T-1

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图 7 复合材料缠绕接头三维实体模型

Figure 7. 3D solid model of composite winding joint

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图 8 复合材料缠绕接头有限元模型约束加载示意图

Figure 8. Schematic of constraint and load for finite element model of composite winding joint

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图 9 碳纤维/环氧树脂复合材料缠绕接头有限元模型载荷-位移曲线

Figure 9. Load-displacement curve of finite element model for carbon fiber/epoxy composite winding joint

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图 10 碳纤维/环氧树脂复合材料缠绕接头第一阶段应力云图

Figure 10. Contour of stress of carbon fiber/epoxy composite winding joint in the first stage

F—Force; U—Displacement

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图 11 碳纤维/环氧树脂复合材料缠绕接头第二阶段胶层损伤演化及对应应力云图

Figure 11. Contour of damage evolution and corresponding stress for adhesive layer of carbon fiber/epoxy composite winding joint in the second stage

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图 12 碳纤维/环氧树脂复合材料缠绕接头第三阶段链环损伤演化过程

Figure 12. Contour of damage evolution for loop plies of carbon fiber/epoxy composite winding joint in the third stage

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图 13 碳纤维/环氧树脂复合材料缠绕接头第三阶段链环应力云图

Figure 13. Contour of stress for loop plies of carbon fiber/epoxy composite winding joint in the third stage

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图 14 碳纤维/环氧树脂复合材料缠绕接头试件T-1~T-4失效模式

Figure 14. Failure modes of carbon fiber/epoxy composite winding joint specimens T-1–T-4

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图 15 碳纤维/环氧树脂复合材料缠绕接头胶层最终损伤形式

Figure 15. Final form of damage for adhesive layer of carbon fiber/epoxy composite winding joint

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表 1 碳纤维/环氧树脂复合材料的性能参数

Table 1 Properties of carbon fiber/epoxy composite

	CCF300/BA9916-Ⅱ	CF3031/BA9916-Ⅱ
E₁₁/GPa	120	60
E₂₂/GPa	7.7	59
E₃₃/GPa	7.7	7.7
μ₁₂=μ₁₃=μ₂₃	0.27	0.05
G₁₂=G₁₃/GPa	5.5	6.4
G₂₃/GPa	5.5	6.4
X_T/MPa	1 400	500
X_C/MPa	1 300	450
Y_T/MPa	35	450
Y_C/MPa	160	455
Z_T/MPa	35	50
Z_C/MPa	160	155
S₁₂=S₁₃/MPa	163	105
S₂₃/MPa	86	83
Notes: E_ii (i, j=1, 2, 3)—Elastic modulus in direction of fibre, perpendicular to fibre in plane and out of plane; X_T, Y_T, Z_T—Tensile strength in the three directions above, respectively; X_C, Y_C, Z_C—Compress strength in the three directions above, respectively; μ_ij, G_ij, S_ij (i, j=1, 2, 3)—Poisson’s ratio, shear modulus and shear strength for 1-2, 1-3, 2-3 plane, respectively.

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表 2 碳纤维/环氧树脂复合材料缠绕接头轴向拉伸试验结果

Table 2 Axial tensile load test results of carbon fiber/epoxy composite winding joint

Specimen number	Failure load/kN	Average load/kN	Coefficient of variation/%
T-1	41.94	41.07	6.49
T-2	38.73
T-3	38.56
T-4	45.06

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表 3 碳纤维/环氧树脂复合材料缠绕接头性能退化方式

Table 3 Degradation modes of carbon fiber/epoxy composite winding joint

Failure mode	Stiffness degradation of material
Tensile fracture of fiber	${E'_{11}} = 0.07{E_{11}}$
Compression fracture of fiber	${E'_{11}} = 0.14{E_{11}}$
Tensile cracking of matrix	${E'_{22}} = 0.2{E_{22}},{G'_{12}} = 0.2{G_{12}},{G'_{23}} = 0.2{G_{23}}$
Compression cracking of matrix	${E'_{22}} = 0.4{E_{22}},{G'_{12}} = 0.4{G_{12}},{G'_{23}} = 0.4{G_{23}}$
Delamination	${E'_{33} } = {G'_{13} } = {G'_{23} } = {v'_{13} } = {v'_{23} } = 0$

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表 4 J-116B结构胶材料属性

Table 4 Material properties of J-116B

$E/{E_{ {\rm{nn} } } }/({\rm{MPa} }{\rm{\cdot m} }{ {\rm{m} }^{ {\rm{ - 1} } } })$	${G_1}/{E_{ {\rm{ss} } } }/({\rm{MPa} }{\rm{\cdot m} }{ {\rm{m} }^{ {\rm{ - 1} } } })$	${G_2}/{E_{ {\rm{tt} } } }/({\rm{MPa} }{\rm{\cdot m} }{ {\rm{m} }^{ {\rm{ - 1} } } })$	$t_{\rm{n}}^0/{\rm{MPa}}$	$t_{\rm{s}}^0/{\rm{MPa}}$	$t_{\rm{t}}^0/{\rm{MPa}}$	${G^{\rm{C} } }/({\rm{J} }{\rm{\cdot} }{ {\rm{m} }^{\rm{ - } } }^{\rm{2} })$
1 000	300	300	20	30	30	2
Notes： $E/{E_{{\rm{nn}}}}$ , ${G_1}/{E_{{\rm{ss}}}}$ , ${G_2}/{E_{{\rm{tt}}}}$ —Interface stiffness for three directions, respectively; $t_{\rm{n}}^0$ , $t_{\rm{t}}^0$ , $t_{\rm{t}}^0$ —Interface strength for three directions, respectively.

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表 5 碳纤维/环氧树脂复合材料缠绕接头部分测点应变仿真值与试验值对比

Table 5 Comparison of simulation and test values of some stain gauges on carbon fiber/epoxy composite winding joint

Strain gauge number	Simulation value/10⁻⁶	Test value/10⁻⁶	Error/%
7	−420	−745	43.62
9	619	479	29.23
11	1 993	1 861	7.09
23	4 124	4 285	3.76
25	1 863	1 754	6.21

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