拉伸载荷下含孔复合材料层合板的力学性能及失效机理

朱浩; 郭章新; 宋鲁彬; 王志华; 李永存

doi:10.11858/gywlxb.2017.04.004

拉伸载荷下含孔复合材料层合板的力学性能及失效机理

doi: 10.11858/gywlxb.2017.04.004

朱浩^{1, 2,},
郭章新^{1, 2,*, ,},
宋鲁彬^{1, 2},
王志华¹,
李永存¹

1.
太原理工大学力学学院材料强度与结构冲击山西省重点实验室，山西太原 030024
2.
西安交通大学机械结构强度与振动国家重点实验室，陕西西安 710049

基金项目:

国家自然科学基金 11602160

国家自然科学基金 11402160

西安交通大学机械结构强度与振动国家重点实验室开放课题 SV2017-KF-01

详细信息

作者简介:
朱浩(1994—), 男，硕士研究生，主要从事复合材料及其结构的力学性能研究.E-mail:571778499@qq.com

通讯作者:
郭章新(1983—), 男，博士，讲师，主要从事复合材料及其结构的力学性能研究.E-mail:woxintanran215@163.com

中图分类号: O346.5
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出版历程
- 收稿日期: 2016-12-29
- 修回日期: 2017-02-27

Mechanical Property and Failure Mechanism of Composite Laminates Containing a Circular Hole under Tension

ZHU Hao^{1, 2
,},
GUO Zhang-Xin^{1, 2,*
, ,},
SONG Lu-Bin^{1, 2},
WANG Zhi-Hua¹,
LI Yong-Cun¹

1.
College of Mechanics, Shanxi Key Laboratory of Material Strength & Structural Impact, Taiyuan University of Technology, Taiyuan 030024, China
2.
State Key Laboratory for Strength and Vibration of Mechanical Structures, Xi'an Jiaotong University, Xi'an 710049, China

摘要

摘要: 采用有限元软件ABAQUS，基于前人提出的失效准则，通过引入纤维损伤因子和基体损伤因子并编制用户材料子程序UMAT，建立了含孔复合材料层合板的三维渐进损伤破坏模型。利用该损伤破坏模型，研究了在轴向拉伸载荷作用下不同圆孔直径和铺层角度的复合材料层合板的纤维和基体的渐进损伤失效过程及规律。结果表明：不同铺层角度条件下，纤维和基体的损伤失效差别较大；圆孔直径和铺设角度对含孔复合材料层合板的失效破坏载荷的影响十分显著，而铺设顺序和开孔位置对失效破坏载荷的影响较小。建立的失效破坏模型能有效地分析层合板的渐进失效破坏过程，为层合板的工程应用和设计提供有益的参考。
- 复合材料层合板 /
- 损伤力学 /
- 渐进失效分析 /
- 数值模拟 /
- UMAT
Abstract: In order to set up a three dimensional damage model for composite laminates with a circular hole, based on the failure criteria proposed by Linde et al., we at first implemented the user-defined material subroutine UMAT in the finite element code ABAQUS using the factors of fiber and matrix to characterize the gradual degradation of material.Then we used the damage model to study the mechanical property and failure mechanism of composite laminates with different ply angels, stacking sequences, hole diameters or positions subjected to uniaxial tension.The results show that the damage factors of the fiber and matrix varied differently for plies with different ply angels.In addition, the hole diameter and ply angle have significant effects on the reaction force of the composite laminates, while the influence of the hole position and stacking sequence of plies are much smaller.Our model can be used to predict qualitatively and quantitatively the progressive failure behavior of composite laminates under tension, thus it can serve as a reference for engineering application and design of composite laminates.
- composite laminates /
- damage mechanics /
- progressive failure analysis /
- numerical simulation /
- UMAT

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图 1 复合材料层合板的几何模型

Figure 1. Geometry of the fiber metal laminates

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图 2 有限元模型

Figure 2. Finite element model

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图 3 不同铺层损伤因子随位移的变化曲线

Figure 3. Variation of damage factor for different plies

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图 4 90°铺层基体损伤因子的渐进损伤失效

Figure 4. Progressive matrix failure contours in 90° ply of composite laminate

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图 5 0°铺层纤维损伤因子的渐进损伤失效

Figure 5. Progressive fiber failure contours in 0° ply of composite laminate

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图 6 复合材料层合板不同孔直径时的载荷-位移曲线

Figure 6. Predicted load vs. displacement of composite laminates with different hole diameters

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图 7 复合材料层合板铺层顺序不同时的载荷-位移曲线

Figure 7. Predicted load vs.displacement curves of composite laminates with different stacking sequences

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图 8 复合材料层合板不同铺设方法的载荷-位移曲线

Figure 8. Predicted load vs. displacement curves of composite laminates for different paving methods

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图 9 复合材料层合板不同开孔位置的载荷-位移曲线

Figure 9. Predicted load vs. displacement curves of composite laminates for different hole positions

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表 1 铝的材料参数

Table 1. Isotropic hardening data for aluminum

σ_Y/(MPa)	ε_p/(%)
300	0
320	0.016
340	0.047
355	0.119
375	0.449
390	1.036
410	2.130
430	3.439
450	5.133
470	8.000
484	14.710

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表 2 层合板的弹性性能及损伤性能参数

Table 2. Orthotropic elastic and damage properties of fiber-enforced epoxy

E_L/(GPa)	E_T/(GPa)	G_LT/(GPa)	G_TT/(GPa)	ν_TT	ν_LT	σ_L^{f, t}/(GPa)	σ_L^{f, c}/(GPa)	σ_T^{f, t}/(MPa)	σ_T^{f, c}/(MPa)	τ_LT^f/(MPa)
55	9.5	5.5	3	0.45	0.33	2.5	2	50	150	50

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