Tensile failure mechanism of carbon fiber reinforced polymer composites with ply splice
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摘要: 对于尺寸较大或形状复杂的结构，通常需要在纤维增强树脂（FRP）复合材料内部对铺层进行拼接处理。铺层拼接会在材料内部引起复杂的应力分布，具有突出的安全隐患。以同一位置处出现不同层数铺层拼接的单向碳纤维增强树脂（CFRP）复合材料为研究对象，重点分析了铺层拼接对材料拉伸力学性能的影响机制。通过拉伸实验，测试了拼接对其力学强度的影响；用相机记录了破坏过程，并结合数字图像相关技术（DIC）对拼接位置附近的应变场进行了监测。利用有限元模型（FEM）模拟和分析结构的破坏机制，采用3D-Hashin准则和渐进损伤模型对CFRP复合材料铺层进行模拟；采用内聚力模型对胶层失效行为进行描述。实验结果表明，拼接结构的引入大幅降低了材料的抗拉强度。FEM模拟与实验测试结果吻合度高，说明了模型的有效性。综合实验结果和模拟分析得到，铺层拼接处产生应力集中，造成被拼接的两部分分离并伴随拼接铺层和连续铺层的层间剪切破坏；层间破坏发生后，拉伸载荷完全由连续铺层承载。因此，材料的最终承载能力由材料中连续铺层数决定。
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关键词:
- 纤维增强树脂复合材料 /
- 拼接铺层 /
- 拉伸 /
- 3D-Hashin /
- 内聚力
Abstract: When facing large scale and complex shapes situations, it is inevitable for fiber reinforced plastics (FRP) to splice two or more plies to meet the requirements. However, the complicated stress distribution within the splice structure may lead to serious safety problems. In this paper, the unidirectional carbon fiber reinforced polymer (CFRP) composite with splicing of different layers at the same location was taken as the research object. The effect mechanism of splicing on the tensile mechanical properties of CFRP composite was emphatically analyzed. The influence of ply splice on its mechanical strength was tested by tensile experiment. The damage process was recorded by camera, and the strain field near the splicing site was monitored by digital image correlation technology (DIC). The finite element model (FEM) was used to simulate and analyze the failure mechanism of the structure, and 3D-Hashin criterion and progressive damage model were used. The failure behavior of adhesive layer was described by cohesive zone model. The results show that the tensile strength of CFRP composite with the ply splice structure decreases obviously. The FEM simulation results agree well with the experimental results, which indicates the effectiveness of the model. According to the experimental results and simulation analysis, the stress concentration at the ply splice results in the separation of two splicing parts and the interlayer shear failure of splicing layer and continuous layer. After the interlaminar failure, the tensile load is completely carried by the continuous layer. Therefore, the ultimate bearing capacity of CFRP composite is determined by the number of continuous layers in the material.-
Key words:
- fiber reinforced plastics /
- ply splice /
- tension /
- 3D-Hashin /
- cohesive zone model
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图 1 含拼接铺层碳纤维增强树脂（CFRP）复合材料示意图
Figure 1. Schematic diagram of carbon fiber reinforced polymer (CFRP) composite with ply splice
图 2 CFRP复合材料拼接位置断层局部放大照片及示意图
Figure 2. Enlarged photos and schematic diagrams of ply splice structures for CFRP composite
图 5 含拼接铺层CFRP复合材料板有限元（FEM）模型
Figure 5. Finite element method (FEM) model of CFRP composites with ply splice (Macroscopic model diagram detail of spliced structural model)
图 6 含拼接铺层CFRP复合材料结构强度随断层数的变化关系
Figure 6. Strength varies with the number of splice of CFRP composite structures
图 7 不同断层CFRP复合材料试样实验荷载-位移曲线
Figure 7. Load-displacement curves of CFRP composite structures with different ply splices
图 8 CFRP复合材料D5试样载荷-变形曲线和破环过程
Figure 8. Load-displacement curves and failure process of CFRP composites specimen D5
图 9 CFRP复合材料D5试样数字图像相关（DIC）及数值模拟纵向应变、剪切应变云图
Figure 9. Image of tensile strain and shear strain of digital image correlation (DIC) technology and FEM of the CFRP composites specimen D5 ((a) Tensile strain eyy of DIC; (b) Tensile strain eyy of FEM; (c) Shear strain exy of DIC; (d) Shear strain exy of FEM)
图 10 CFRP复合材料D5试样界面单元、纤维单元损伤演化及拉伸、剪切应力云图
Figure 10. Damage evolution, tensile stress and shear stress images of cohesive elements and CFRP composite elements of the CFRP composites specimen D5 ((a) SDEG of cohesive elements; (b) SDEG of CFRP elements; (c) Tensile stress S11; (d) Shear stress S13)
表 1 T300/E901 CFRP复合材料力学性能和强度参数
Table 1. Material properties and strength parameters of T300/E901 CFRP composites
Material Mechanical parameters Value Epoxy resin E901 E/GPa 3.78 ν 0.35 Unidirectional CFRP E1/GPa 127.34 E2/GPa 7.78 E3/GPa 7.78 ν12 0.27 ν13 0.27 ν23 0.42 G12/GPa 5.00 G13/GPa 5.00 G23/GPa 3.08 Xt/MPa 2 114 Xc/MPa 704 Yt/MPa 80 Yc/MPa 68 S12=S13/MPa 80 S23/MPa 55 Notes: E—Young’s modulus; ν—Poisson's ratio; G—Shear modulus; X, Y—Strength; Subscript 1, 2 and 3—Direction 1, 2 and 3; Subscript t—Tension; Subscript c—Compression. 
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表 2 含拼接铺层CFRP复合材料分层起始载荷FEM模拟值与实验均值对比
Table 2. Comparison of initial damage loads of experiment and FEM for CFRP composites with ply splice
Initial damage load
for experiment/NInitial damage load
for FEM/NError/% D3 38 936.94 43 473.7 11.6 D5 30 243.57 32 568.5 7.6 D7 26 098.17 25 489.1 6.4
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表 3 含拼接铺层CFRP复合材料极限载荷EMF模拟值与实验均值对比
Table 3. Comparison of ultimate loads of experiment and FEM for CFRP composites with ply splice
Ultimate load for experiment/N Ultimate load for FEM/N Error/% D0 63 731.48 62 850.3 1.7 D3 47 655.43 55 253.5 16.1 D5 41 354.25 45 521.9 10.1 D7 40 472.96 40 627.3 0.3
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