压剪载荷比对CFRP层合板失效行为影响的数值研究

骈瑢; 石晓飞; 马文渊; 刘丰睿; 王林娟; 赵丽滨

压剪载荷比对CFRP层合板失效行为影响的数值研究

骈瑢^{1, 2},
石晓飞³,
马文渊³,
刘丰睿^{1, 2, ,},
王林娟^{1, 2},
赵丽滨^{4, 5, 6}

1.
北京航空航天大学宇航学院, 北京 100191
2.
航天器设计优化与动态模拟技术教育部重点实验室, 北京 100191
3.
海鹰航空通用装备有限责任公司, 北京 100074
4.
河北工业大学机械工程学院, 天津 300401
5.
先进智能防护装备技术教育部重点实验室, 天津 300401
6.
河北省跨尺度智能装备技术重点实验室, 天津 300401

基金项目: 国家自然科学基金(12072005，U23 A2067)；河北省全职引进高端人才科研项目(2021 HBQZYCSB009)

详细信息

通讯作者:
刘丰睿，博士，副教授，博士生导师，研究方向为复合材料结构强度分析　E-mail: frliu@buaa.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: 2024-07-15
- 修回日期: 2024-08-12
- 录用日期: 2024-08-25
- 网络出版日期: 2024-09-07

Numerical study of the effect of compression-shear load ratio on the failure behavior of CFRP laminated plate

PIAN Rong^{1, 2},
SHI Xiaofei³,
MA Wenyuan³,
LIU Fengrui^{1, 2
, ,},
WANG Linjuan^{1, 2},
ZHAO Libin^{4, 5, 6}

1.
School of Astronautics, Beihang University, Beijing 100191, China
2.
Ministry of Education Key Laboratory of Spacecraft Design Optimization & Dynamic Simulation, Beihang University, Beijing 100191, China
3.
HiWing Aviation General Equipment Co., Ltd, Beijing 100074, China
4.
School of Mechanical Engineering, Hebei University of Technology, Tianjin 300401 China
5.
Key Laboratory of Advanced Intelligent Protective Equipment Technology, Ministry of Education, Tianjin 300401, China
6.
Key Laboratory of Hebei Province on Scale-pan Intelligent Equipment Technology, Tianjin 300401 China

Funds: National Natural Science Foundation of China (No.12072005 and U23 A2067); Project of High-Level Talents Introduction of Hebei Province (No.2021 HBQZYCSB009)

摘要

摘要: 碳纤维增强(Carbon fiber reinforced polymer, CFRP)复合材料层合板是飞行器中的常用结构。面内压缩和剪切载荷下，层合板结构失效同时受屈曲和材料损伤影响，失效形式复杂多变。本文建立了考虑就地效应、横向应力对剪切强度的影响以及剪切非线性的渐进损伤失效分析方法，开展压剪试验对分析方法进行了验证，并在此基础上研究了不同压缩和剪切载荷比下CFRP层合板的失效行为。研究表明，压剪载荷比低时，层合板先发生材料的初始损伤，然后达到最大载荷；压剪载荷比高时，直接发生屈曲，同时达到最大载荷，不发生材料损伤；载荷比处于两者之间时，先发生材料损伤，然后屈曲并且达到最大载荷。此外，压剪载荷比的变化还会对层合板的压缩承载能力、剪切承载能力、以及结构达到最大载荷时的损伤扩展程度产生影响。
- 复合材料层合板 /
- 压剪载荷 /
- 渐进损伤 /
- 试验验证 /
- 载荷比例
Abstract: Carbon fiber reinforced polymer (CFRP) composite laminated plates are commonly used structures in the aircraft. Under in-plane compression-shear loads, the failure of laminated plates is affected by both buckling and material damage, and the failure forms are complex and variable. In this paper, a progressive damage analysis method was established considering the in-situ effect, the influence of transverse stress on shear strength, and the shear nonlinearity of the material. The compression-shear test was carried out to validate the proposed method. Based on the validated method, the failure behavior of the CFRP plates with different compression-shear load ratios was investigated based on the finite element model. It is shown that when the compression-shear loads ratio is low, the initial material damage of the plate occurs first, and then the maximum load is reached. When the load ratio is high, buckling occurs directly, and at the same time, the maximum load is reached without material damage. When the load ratio is in between, material damage occurs first, then buckling occurs and maximum load is reached. In addition, the change of compression-shear load ratio will also have an effect on the compression and shear load bearing capacity of the plate, and the damage extension degree of the plate when the maximum load is reached.
- composite laminated plate /
- compression-shear load /
- progressive damage /
- experimental validation /
- load ratio

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图 1 试验件尺寸示意图

Figure 1. Schematic diagram of specimen dimensions

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图 2 试验加载示意图

Figure 2. Schematic diagram of test

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图 3 试验件数值模型

Figure 3. Numerical model of the specimen

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图 4 碳纤维增强(CFRP)层合板剪切非线性系数拟合

Figure 4. Shear nonlinear coefficient fitting of the carbon fiber reinforced polymer (CFRP) plates

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图 5 试验件正反面中心点应变-载荷曲线

Figure 5. The strain-load curves at the center point of the front and back faces of the specimen

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图 6 数值模拟得到的试验件载荷位移曲线

Figure 6. The load-displacement curve obtained by numerical simulation of the specimen

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图 7 试验件结构中心点的面外位移-载荷曲线

Figure 7. The Out-of-plane displacement-load curve at the center of the structure the specimen

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图 8 数值模拟结果与试验结果中的失效位置对比

Figure 8. Comparison of the numerical and experimental failure locations

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图 9 各载荷比下的CFRP层合板载荷位移曲线

Figure 9. Load-displacement curves at various load ratios of CFRP plates

η is the ratio of the compression load to the shear load

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图 10 CFRP层合板各载荷随压剪载荷比的变化

Figure 10. Variation of each load with the compression-shear load ratio of CFRP plates

η is the ratio of the compression load to the shear load; N_x is the compression component of the loads; N_xy is the shear component of the loads

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图 11 本文结构在不同载荷比下的屈曲模态

Figure 11. Buckling modes of the structure under different compression-shear load ratios

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表 1 USN15000/EPW材料参数

Table 1. Properties of the USN15000/EPW material

E₁/GPa	E₂/GPa	v₁₂		G₁₂/GPa
129.96	9.62	0.35		4.99

X_T/MPa	X_C/MPa	Y_T/MPa	Y_C/MPa	S₁₂/MPa
1564	997	44	180	77

G_IC/(N/mm)	G_IIC/(N/mm)	c_f	E_m/GPa	G_m/GPa
129.96	9.62	70%	3.52	1.2
Notes：E₁, E₂, v₁₂, and G₁₂ are the stiffness properties of the material; X_T, X_C, Y_T, Y_C, and S₁₂ are the strength properties of the material; G_IC and G_IIC are the fracture toughness of the material; c_f is the fiber volume fraction; E_m and G_m are the stiffness properties of the matrix.

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表 2 数值模拟方法验证与对比

Table 2. Validation and comparison of two numerical simulation methods

Method	Buckling		Initial damage		Max load
Method	Load/N	Err/%	Load/N	Err/%	Load/N	Err/%
Test	402	−	1509	−	1627	−
Previous	425	5.72	761	−49.57	1792	10.14
Present	424	5.47	1653	9.54	1816	11.62

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表 3 各工况下层合板失效扩展情况和载荷比

Table 3. Damage initiation and extension each loading conditions

η	Damage type		Initial damage load/ Maximum load
η	Initial damage	Ultimate failure	Initial damage load/ Maximum load
0	FC, FM	FC, FM	0.994
0.1	FC, FM	FC, MC, FM	0.903
0.5	FC, FM	FC, MC, FM, IT	0.846
1	FC, FM	FC, MC, FM	0.990
2	Undamaged	Undamaged	−
10	Undamaged	Undamaged	−
∞	Undamaged	Undamaged	−
Notes: η is the ratio of the compression load to the shear load.

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