Failure mechanisms of composite laminate subjected to edge-on impact
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摘要: 低速冲击复合材料层合板结构的自由边缘会严重威胁其安全性。本文对T700/YPH307复合材料层合板进行了边缘冲击试验与数值仿真研究。试验中通过目视检测、超声C扫描、电子显微观测及X-ray计算机断层扫描(CT)技术检测了层合板边缘冲击后的损伤状态，揭示了不同边缘冲击能量下，材料内部损伤的三维空间分布形貌。基于Mohr失效面理论，建立了一种考虑各向异性材料断裂面角度的连续介质损伤力学模型，同时结合内聚力模型综合表征了层合板边缘受低速冲击时层内纤维基体损伤与层间分层的起始、扩展和耦合细节。数值预测结果与试验值吻合较好，表明边缘冲击失效机制主要包括两种典型特征，即极限冲击力时形成冲头下方局部碎片楔及稳定波动阶段因楔入作用造成的外侧子层弯曲断裂。此外，边缘冲击能量越高，层合板内部损伤越严重，而铺层顺序对边缘冲击响应与损伤形貌影响相对有限。
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关键词:
- 复合材料 /
- 边缘冲击 /
- 失效机制 /
- 连续介质损伤力学模型 /
- 损伤重构
Abstract: Low velocity impact on the structural free edge would threaten the safety of laminated composite structures. In this paper, experimental and numerical investigations were conducted to study the edge-on impact behaviors of T700/YPH307 composite laminates. Visual inspection, ultrasonic C-scanning, electron microscopy and X-ray computed tomography (CT) technique were performed to detect the post-impact damage status of composite laminates subjected to edge-on impact, which could further reveal 3D spatial distribution of internal damage. Based on the Mohr's theory of fracture plane, a continuum damage mechanics model, considering fracture plane angle within anisotropic materials, was established. And with combination of cohesive zone model, the initiation, propagation and interaction of complicated edge-on impact damage modes, i.e. intra-laminar fiber and matrix failure and inter-laminar delamination, could be characterized in detail. There is a good agreement between numerical and experimental results. It is suggested that failure mechanisms induced by edge-on impact mainly include two distinct characteristics, namely the generation of localized debris wedge beneath the impactor corresponding to peak value of impact force, and the bending fracture of outer plies due to the wedge effect at the stage of stable fluctuations in impact force. Furthermore, it is found that the internal damage would be more serious with the impact energy increasing, while stacking sequence has a relatively small influence on the edge-on impact responses and damage morphology. -
图 3 Xradia 620 Versa Micro-CT检测系统与边缘冲击损伤三维重构区域
Figure 3. Xradia 620 Versa Micro-CT detecting system and three-dimensional reconstruction area of edge-on impact induced damage
图 4 复合材料层合板边缘冲击力学响应
Figure 4. Mechanical responses of composite laminates subjected to edge-on impact
图 5 边缘冲击后层合板目视损伤形貌
Figure 5. Visual inspection of edge-on impact damage within the composite laminates
图 6 复合材料层合板冲击边缘处纵向长裂纹的光学显微镜检测
Figure 6. Optical microscope detection of a long longitudinal crack on the impacted edge of composite laminates
图 7 超声C扫描检测的复合材料层合板典型分层投影
Figure 7. Typical delamination projection of composite laminates detected by ultrasonic C-scanning
图 8 基于X-ray CT的复合材料层合板典型边缘冲击损伤形貌
Figure 8. Typical edge-impact damage morphology of composite laminates based on X-ray CT
图 9 边缘冲击复合材料层合板有限元模型(FEM)及边界条件
Figure 9. Finite element model (FEM) and boundary condition of composite laminate subjected to edge-on impact
Uy—Displcement in y direction; Uz—Displcement in z direction
图 10 有限元预测的T700/YPH-07复合材料层合板冲击力-位移曲线与试验结果的比较
Figure 10. Comparison between numerical and experimental results of impact force-displacement curves for T700/YPH-07 composite laminates
图 11 T700/YPH-07复合材料层合板边缘冲击点的表面损伤形貌
Figure 11. Damage morphology of the edge surface near the impacted site for T700/YPH-07 composite laminates
U, U2—Displacement in y direction (mm)
图 12 T700/YPH-07复合材料层合板C扫描与有限元模型得到的分层投影对比
Figure 12. Comparisons of projected delamination area obtained by C-scanning and FEM for T700/YPH-07 composite laminates
图 13 T700/YPH-07复合材料层合板边缘冲击分层的空间分布
Figure 13. Spatial distribution of edge-on impact induced delamination for T700/YPH-07 composite laminates
图 14 T700/YPH-07复合材料层合板边缘冲击引入层内损伤的X-ray CT观测与有限元模拟结果
Figure 14. X-ray CT and FEM numerical results of intra-laminar damage caused by edge-on impact for T700/YPH-07 composite laminates
FFC—Fiber compression fracture; IFFT—Inter-fiber tension fracture; IFFC—Inter-fiber compression fracture; SDV—Solution dependent variables
图 15 T700/YPH-07复合材料层合板不同截面上的边缘冲击损伤形貌
Figure 15. Edge-on impact induced damage morphology at different cross-sections for T700/YPH-07 composite laminates
IFF—Inter-fiber fracture; FF—Fiber fracture
图 16 T700/YPH-07复合材料层合板在边缘冲击下的内部损伤演化
Figure 16. Evolution of internal damage within the T700/YPH-07 composite laminate under edge-on impact
表 1 边缘冲击试件的铺层参数
Table 1. Lay-up parameters of the specimens subjected to edge-on impact
Specimen Type Lay-up Ply number QI Quasi-isotropic [45/0/−45/90]4S 32 CP Cross-ply [902/02]4S 32 
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表 2 T700/YPH-07复合材料力学性能参数
Table 2. Material properties used for T700/YPH-07 composite
E11/GPa E22=E33/GPa G12=G13/GPa v12(v13) Xt/MPa Xc/MPa Yt/MPa Yc/MPa 121 8 4 0.3 2497 1064 46 109 S12/MPa Kn=Ks=Kt/
(N·mm−3)tn/MPa ts (tt)/MPa ${G_{ {\text{IC} } } }$/(kJ·m−2) ${G_{ {\text{IIC} } } }$/(kJ·m−2) $ G_{1 {\rm{c}}}^t $/(kJ·m−2) $ G_{1 {\rm{c}}}^{\rm{c}} $/(kJ·m−2) 66 106[28] 19.5 22.8 0.32 1.1 95[13] 133.3[13] Notes: E11 and E22 (E33)—Longitudinal and transverse elastic moduli; G12 (G13)—In-plane shear modulus; v12 (v13)—Poisson's ratio; Xt and Xc—Longitudinal tensile and compressive strengths; Yt and Yc—Transverse tensile and compressive strengths; S12—In-plane shear strength; Kn (Ks, Kt)—Penalty stiffness of cohesive elements; tn and ts (tt)—Interfacial strengths; ${G_{ {\text{IC} } } }$ and ${G_{ {\text{IIC} } } }$—Critical fracture energy release rates for mode I and mode II, respectively; $ G_{1 {\rm{c}}}^{\rm{t }}$ and $ G_{1 {\rm{c}}}^{\rm{c}} $—Critical fracture energy release rates for fiber tensile and compressive fracture.
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表 3 T700/YPH-07复合材料层合板典型冲击阶段冲击力的有限元预测值与试验测量值
Table 3. FEM predictions and experimental measurements of impact force for T700/YPH-07 composite laminates during typical edge-on impact stages
Lay-up Energy/(J·mm−1) Fp /N Fm /N Test FEM Test FEM QI 1.5 8953 9742 7398 4961 3.0 8996 9110 6560 5698 CP 1.5 7505 8516 5131 5345 3.0 8779 9646 6608 5743 Notes: Fp and Fm—Forces corresponding to peak value and average value of the loading plateau, respectively.
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表 4 T700/YPH-07复合材料层合板C扫描与有限元预测损伤面积
Table 4. Delamination area obtained by C-scanning and FEM for T700/YPH-07 composite laminates
Lay-up Energy/(J·mm−1) Damaged area/mm2 Error/% Test Simulation QI 1.5 384 427 11.2 3.0 952 912 −4.2 CP 1.5 433 431 −0.5 3.0 832 767 −7.8
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