复合材料层合板自由边缘冲击失效机制

钟小丹; 李朝阳; 李念; 叶强; 居程

复合材料层合板自由边缘冲击失效机制

钟小丹¹,
李朝阳²,
李念^2, ,,
叶强³,
居程²

1.
沈阳飞机设计研究所, 沈阳 110035
2.
南京工业大学　机械与动力工程学院, 南京 211816
3.
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

基金项目: 国家自然科学基金 (基金号11802116)

详细信息

通讯作者:
李念，博士，副教授，硕士生导师，研究方向为复合材料结构设计与分析　E-mail: linian@njtech.edu.cn

中图分类号: TB332
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- 被引次数: 0
出版历程
- 收稿日期: 2022-10-31
- 修回日期: 2023-01-16
- 录用日期: 2023-02-03
- 网络出版日期: 2023-02-27

Failure mechanisms of composite laminate subjected to edge-on impact

1.
Shenyang Aircraft Design Research Institute, Shenyang 110035, China
2.
College of Mechanical and Power Engineering, Nanjing Tech University, Nanjing 211816, China
3.
State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Funds: National Natural Science Foundation of China (11802116)

摘要

摘要: 当复合材料层合板的自由边缘遭受局部低速冲击后，相同冲击能量引起的损伤程度比面外冲击更为严重，且边缘冲击产生的严重强度降将可能对结构安全性造成灾难性打击。迄今为止，大量论述复合材料低速冲击损伤阻抗与损伤容限的工作局限于冲击位置远离边缘的冲击事件，对边缘冲击失效机制和相互作用规律的认识尚不充分。为确保复合材料结构运营安全，同时鉴于边缘冲击失效机制对剩余强度的评估与后续检测方法的选择至关重要，亟需开展复合材料边缘冲击失效机制方面的基础工作。本文以T700/YPH307复合材料层合板为研究对象，采用试验研究与数值模拟并行的研究手段，揭示2种冲击能量(1.5J/mm和3J/mm)下不同铺层层合板在其自由边缘受到低速冲击时的力学响应和失效机制。试验中结合冲击表面的目视检测、超声C扫描、电子显微观测以及三维X-ray计算机断层扫描(CT)技术对边缘冲击损伤的三维空间分布情况进行宏细观表征。针对复合材料层内纤维与基体损伤，发展了基于Mohr失效面理论的连续介质损伤力学模型，并采用粘聚区模型预测分层的起始与扩展，建立了适用于纤维增强复合材料边缘冲击失效分析模型。结果表明：边缘冲击损伤呈现高度局部化特征，除了基体开裂与大面积分层外，典型损伤包括纤维压缩断裂以及冲头挤压下纤维基体压裂堆积形成碎片楔。碎片楔的产生决定了极限冲击力，外侧子层弯曲断裂导致了冲击力的稳定波动。此外增加冲击能量会使得边缘冲击损伤越严重，但是铺层顺序对边缘冲击响应与损伤影响相对有限。1有限元预测不同截面上的边缘冲击损伤形貌与试验观测比较
- 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.
- composite /
- edge-on impact /
- failure mechanism /
- continuum damage mechanics model /
- damage reconstruction

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图 1 复合材料层合板边缘冲击试验夹具

Figure 1. Edge-on impact fixture for composite laminates

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图 2 CEAST 9350落锤式冲击试验机

Figure 2. Instron CEAST 9350 drop-weight tower

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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

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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

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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

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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

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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

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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

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图 9 边缘冲击复合材料层合板有限元模型及边界条件

Figure 9. FE model and boundary condition of composite laminate subjected to edge-on impact

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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

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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

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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

Figure 12. Comparisons of projected delamination area obtained by C-scanning and FE model for T700/YPH-07 composite laminates

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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

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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 numerical results of intra-laminar damage caused by edge-on impact for T700/YPH-07 composite laminates

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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

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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

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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 No.	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)	X_t/MPa	X_c/MPa	Y_t/MPa	Y_c/MPa
121	8	4	0.3	2497	1064	46	109

S₁₂/MPa	K_n(=K_s=K_t)/ (N·mm⁻³)	t_n/MPa	t_s(t_t)/MPa	$ {G_{{\text{Ic}}}} $/(kJ·m⁻²)	$ {G_{{\text{IIc}}}} $/(kJ·m⁻²)	$ G_{1 c}^t $/(kJ·m⁻²)	$ G_{1 c}^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) are longitudinal and transverse elastic moduli; G₁₂ (G₁₃) is in-plane shear modulus; v₁₂(v₁₃) is poisson’s ratio; X_t and X_c are longitudinal tensile and compressive strengths; Y_t and Y_c are transverse tensile and compressive strengths; S₁₂ is in-plane shear strength; K_n(=K_s=K_t) is the penalty stiffness of cohesive elements; t_n and t_s(t_t) are interfacial strengths; $ {G_{{\text{Ic}}}} $ and $ {G_{{\text{IIc}}}} $ are the critical fracture energy release rates for Mode-I and Mode-II, respectively; $ G_{1 c}^t $ and $ G_{1 c}^c $ are the 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)	F_m/N		F_p/N
Lay-up	Energy/(J·mm⁻¹)	Test	FEM	Test	FEM
QI	1.5	8953	9742	7398	4961
QI	3	8996	9110	6560	5698
CP	1.5	7505	8516	5131	5345
CP	3	8779	9646	6608	5743
Notes: F_m and F_p denote the 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/%
Lay-up	Energy/(J·mm⁻¹)	Test	Simulation	Error/%
QI	1.5	384	427	11.2
QI	3.0	952	912	−4.2
CP	1.5	433	431	−0.5
CP	3.0	832	767	−7.8

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