Tensile bearing behavior of composite structures considering filament wound morphology
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摘要: 纤维缠绕复合材料的纤维束具有交叉起伏形态特征，该形态对复合材料结构的力学行为有显著的影响。本文采用数值仿真和实验手段研究了纤维缠绕复合材料平板结构的拉伸力学行为。实验方面，开展纤维缠绕复合材料平板的准静态拉伸实验，通过数字图像相关技术(DIC)监测其表面应变场的演化过程，研究交叉起伏特征对载荷-位移曲线和应变分布特征的影响；数值分析方面，构建包含纤维缠绕形态的介观有限元模型，基于3D Hashin失效准则开展渐进损伤过程模拟，并引入了复合材料的剪切非线性行为。选取层合板结构为参照组，同时开展实验和数值分析。实验结果表明：对于层合结构，缠绕结构的整体刚度更低，失效位移更大，失效载荷基本相同，且缠绕结构菱形特征单元中部纤维交叉起伏区域存在明显的应变集中现象。所构建的有限元模型和实验结果吻合较好，呈现出纤维起伏区域的应变集中、失效起始和扩展行为。Abstract: Fiber bundles of filament wound structure have the morphology characteristic of crossover and undulation, which has significant impact on the mechanical behavior of composite structures. In this research, the tensile mechanical behavior of filament wound composite plate was investigated by numerical and experimental methods. In experimental study, quasi-static tensile experiment of fiber-wound composite plate was carried out, and the evolutions of surface strain field were recorded by digital imaging correlation (DIC). The influences of crossover and fluctuation characteristics on the load-displacement curve and strain distribution were investigated. For the numerical analysis, a meso-scale finite element model was created based on the filament wound morphology. The progressive failure process was simulated based on 3D Hashin failure criterion, and the nonlinear shearing behavior of composites was also involved. The experimental and numerical studies of laminated structures were also carried out as the reference group. The experimental results indicate that, compared with the laminated structures, the filament wound structure gives a lower stiffness, a larger failure displacement, and almost a same failure load. An obvious strain concentration is observed in the fiber crossover and undulating region which locates at the middle area of the filament wound rhombus unit. The finite element analysis results are in good agreement with the experimental ones. The strain concentration in the fiber fluctuation region, as well as the failure initiation and propagation behaviors, are represented properly by the numerical analysis.
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图 2 T300碳纤维/环氧树脂复合材料预浸料固化温度和压力时程曲线
Figure 2. Curing temperature and pressure curves of T300 carbon fiber/epoxy resin composite prepreg
图 4 实验方法示意图
DIC—Digital imaging correlation
Figure 4. Schematic diagram of experimental method
图 5 缠绕结构复合材料纤维束起伏示意图
Figure 5. Fiber crossover and undulation diagram of filament wound structure composite
图 6 缠绕结构复合材料有限元模型组成图
Figure 6. Composition diagram of filament wound structure composite finite element model
图 7 T300碳纤维/环氧树脂复合材料拉伸载荷-位移曲线
FEM—Finite element model
Figure 7. Tensile load-displacement curves of T300 carbon fiber/epoxy resin composites
图 8 T300碳纤维/环氧树脂复合材料试样破坏形态
Figure 8. Failure pattern of T300 carbon fiber/epoxy resin composite specimens
图 9 T300碳纤维/环氧树脂复合材料层合结构拉伸实验过程应变场变化
εxx—Horizontal strain; εyy—Vertical strain
Figure 9. Variation of strain field during tensile test of T300 carbon fiber/epoxy resin composite laminated structure
图 10 T300碳纤维/环氧树脂复合材料缠绕结构实验过程应变场变化
Figure 10. Variation of strain field during tensile test of T300 carbon fiber/epoxy resin composite wound structure
图 11 T300碳纤维/环氧树脂复合材料层合结构有限元仿真应变场变化
Figure 11. Variation of strain field in finite element simulation of T300 carbon fiber/epoxy resin composite laminated structure
图 12 T300碳纤维/环氧树脂复合材料缠绕结构有限元仿真应变场变化
Figure 12. Variation of strain field in finite element simulation of T300 carbon fiber/epoxy resin composite wound structure
图 13 实验与仿真所得T300碳纤维/环氧树脂复合材料缠绕结构竖直方向应变(εyy)的曲面图
Δy—Loading displacement
Figure 13. Surface diagrams of the vertical strain (εyy) of T300 carbon fiber/epoxy resin composite wound structure obtained from experiment and simulation
图 14 缠绕结构中显微镜下纤维束交叉起伏截面图
Figure 14. Cross undulating section image of fiber bundle captured by microscope in wound structure
图 15 缠绕结构中的纤维伸展(a)和偏转(b)示意图
Figure 15. Schematic diagram of fiber stretching (a) and rotation (b) in wound structure
图 16 T300碳纤维/环氧树脂复合材料缠绕结构应力云图
Figure 16. Stress contour of T300 carbon fiber/epoxy resin composite wound structure
图 17 T300碳纤维/环氧树脂复合材料层合结构应力云图
Figure 17. Stress contour of T300 carbon fiber/epoxy resin composite laminated structure
图 18 T300碳纤维/环氧树脂复合材料缠绕结构基体拉伸损伤过程
Figure 18. Matrix tensile damage process of T300 carbon fiber/epoxy resin composite wound structure
图 19 T300碳纤维/环氧树脂复合材料缠绕结构纤维交叉起伏区域纤维方向应力(σ11) 云图
Figure 19. Fiber directional stress (σ11) nephogram of fiber cross fluctuation area of T300 carbon fiber/epoxy resin composite wound structure
图 20 T300碳纤维/环氧树脂复合材料层合结构纤维方向应力(σ11)云图
Figure 20. Fiber directional stress (σ11) nephogram of T300 carbon fiber/epoxy resin composite laminated structure
表 1 试样编号和数量
Table 1. Lable and number of samples
Lable Number of sample FWC 3 SLC 3 Notes: FWC—Filament wound composites; SLC—Standard laminate composites. 
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表 2 T300碳纤维/环氧树脂复合材料预浸料材料参数
Table 2. Material properties of T300 carbon fiber/epoxy resin composite prepreg
Parameter Value E11/GPa 127.0 E22/GPa 7.9 E33/GPa 7.9 μ12 0.35 μ13 0.35 μ23 0.45 G12/GPa 2.1 G13/GPa 2.1 G23/GPa 4.8 XT/GPa 2.0 XC/GPa 1.2 YT/MPa 38.5 YC/MPa 180.7 S/MPa 135.0 Gft/(N·mm-1) 133 Gfc/(N·mm-1) 60 Gmt/(N·mm-1) 0.352 Gmc/(N·mm-1) 1.450 Notes: E—Elastic modulus; μ—Poisson's ratio; G—Shear modulus; 1—Direction of fiber; 2—Direction of matrix; 3—Thickness direction of layer; XT—Longitudinal tensile strength; XC—Longitudinal compressive strength; YT—Transverse tensile strength; YC—Transverse compressive strength; S—In-plane shear strength; Gft, Gfc, Gmt, Gmc—Critical value of strain energy release rate.
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表 4 内聚力单元界面性能参数
Table 4. Interface performance parameters of cohesive element
Parameter Value TI/MPa 48.0 TII/MPa 79.0 K/(N·mm–2) 106 GIC/(N·mm–1) 0.128 GIIC/(N·mm–1) 0.653 Notes: TI, TII—Mode I/II strength; K—Interface stiffness; GIC, GIIC—Critical strain energy release rates.
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表 5 T300碳纤维/环氧树脂复合材料实验结果比较
Table 5. Comparison of experimental results of T300 carbon fiber/epoxy resin composites
Structure Ultra load/kN Failure displacement/mm FWC 5.2 2.7 SLC 5.2 1.8
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