含孔玻璃纤维/环氧树脂复合材料-铝合金层板的拉伸损伤行为与热暴露响应

谢波涛; 高亮; 江帅; 李梦军

doi:10.13801/j.cnki.fhclxb.20200211.001

含孔玻璃纤维/环氧树脂复合材料-铝合金层板的拉伸损伤行为与热暴露响应

doi: 10.13801/j.cnki.fhclxb.20200211.001

长春工业大学　先进结构材料教育部重点实验室，长春 130012

基金项目: 国家自然科学基金(11502031)；2019年吉林省预算内基本建设资金(产业技术研究与开发)计划项目(2019C046-6)

详细信息

通讯作者:
高亮，博士，副教授，研究方向为轻质复合材料及结构多功能一体化　E-mail：gaol@ccut.edu.cn

中图分类号: TB332
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出版历程
- 收稿日期: 2019-12-27
- 录用日期: 2020-02-02
- 网络出版日期: 2020-02-12
- 刊出日期: 2020-11-15

Tensile damage behavior and thermal exposure response of glass fiber/epoxy composite-aluminum alloy laminates with an open-hole

Key Laboratory of Advanced Structural Materials, Ministry of Education, Changchun University of Technology, Changchun 130012, China

摘要

摘要: 采用试验和数值方法研究了含孔玻璃纤维/环氧树脂(GF/EP)复合材料-铝合金层板在不同热暴露温度下的拉伸剩余强度和损伤失效模式，揭示了层间损伤、纤维损伤及基体损伤的演化过程。结果表明：随着热暴露温度升高，含孔GF/EP复合材料-铝合金层板剩余强度不断下降，拉伸破坏呈现出明显的纤维断裂与层间分层混合失效模式。热暴露温度越高或开孔直径越大，GF/EP复合材料-铝合金层板的层间分层损伤区域越小。随着载荷的增大，沿加载方向的0°纤维和基体的损伤分别呈现出类似“漏斗”形和“花瓣”状的损伤演化形式，而层间损伤区域呈现出一对相对开孔对称的三角形损伤演化形式。基于GF/EP复合材料-铝合金层板的剩余强度和损伤失效模式的数值仿真与试验结果吻合较好。
- 玻璃纤维/环氧树脂复合材料-铝合金层板 /
- 热暴露 /
- 拉伸性能 /
- 剩余强度 /
- 损伤模式
Abstract: The tensile residual strength and damage mode of glass fiber/epoxy (GF/EP) composite-aluminum alloy laminates with an open-hole subjected to different thermal exposure temperatures were studied based on experimental and numerical methods, revealing the evolution process of various failure including interlaminar damage, fiber damage and matrix damage. The results show that residual strength of GF/EP composite-aluminum alloy laminates with an open-hole gradually decreases as the thermal exposure temperature increases, followed by a mixed failure mode with fiber fracture and interlaminar delamination. The increasing temperature and open-hole diameter can both lead to a reduction of interlaminar damage area. As the load increases, 0° fiber along the loading direction shows a funnel-shaped damage evolution form, and petal shape for matrix damage. The interlaminar damage presents a pair of symmetrical triangles region with respect to the open-hole. The numerical results show good agreement with test ones based on residual strength and failure mode of GF/EP composite-aluminum alloy laminates.
- glass fiber/epoxy composite-aluminum alloy laminate /
- thermal exposure /
- tensile property /
- residual strength /
- damage mode

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图 1 GF/EP复合材料-铝合金层板铺层设计

Figure 1. Layup design of GF/EP composite-aluminum alloy laminate

L—Longitudinal; T—Transverse

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图 2 GF/EP复合材料-铝合金层板固化工艺

Figure 2. Curing process for GF/EP composite-aluminum alloy laminate

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图 3 GF/EP复合材料-铝合金层板制备工艺流程

Figure 3. Preparation process of GF/EP composite-aluminum alloy laminate

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图 4 含圆形孔GF/EP复合材料-铝合金层板试样示意图

Figure 4. Schematic diagram of GF/EP composite-aluminum alloy laminate with an open-hole

D—Diameter

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图 5 含孔GF/EP复合材料-铝合金层板单向拉伸数值模型

Figure 5. Numerical model of unidirectional tensile of GF/EP composite-aluminum alloy laminate with an open-hole

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图 6 不同热暴露温度下GF/EP复合材料-铝合金层板的应力-应变曲线及剩余强度随直径的变化曲线

Figure 6. Stress-strain curves and variation curves of residual strength with diameter of GF/EP composite-aluminum alloy laminates at different thermal exposure temperatures

FEA—Finite element analysis; D—Open-hole diameter

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图 7 GF/EP复合材料-铝合金层板试验与仿真应力-应变曲线

Figure 7. Experimental and numerical stress-strain curves of GF/EP composite-aluminum alloy laminates

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图 8 含孔GF/EP复合材料-铝合金层板试件拉伸断裂失效

Figure 8. Tensile fracture of GF/EP composite-aluminum alloy laminates with an open-hole

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图 9 含孔GF/EP复合材料-铝合金层板层间损伤的温度响应

Figure 9. Temperature response of interlaminar damage of GF/EP composite-aluminum alloy laminates with an open-hole

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表 1 2024-T3铝合金材料性能

Table 1. Material properties of aluminum 2024-T3

Young’s modulus E/GPa	Shear modulus G/GPa	Poisson’s ratio ν	Thickness t/mm
72	27	0.33	0.5

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表 2 玻璃纤维/环氧树脂(GF/EP)预浸料材料性能

Table 2. Mechanical properties of glass fiber/epoxy (GF/EP) prepreg

Parameter	Value
Longitudinal stiﬀness E₁₁/GPa	48.75^a
Transverse stiﬀness E₂₂/GPa	14.33^a
Out-of-plane stiﬀness E₃₃/GPa	14.33^a
Poisson’s ratio ν₁₂, ν₁₃	0.252^a
Poisson’s ratio ν₂₃	0.32^a
Shear modulus G₁₂, G₁₃/MPa	5 100^a
Shear modulus G₂₃/MPa	5 100^a
Longitudinal tensile strength X_T/MPa	1 280^b
Longitudinal compressive strength X_C/MPa	800^b
Transverse tensile strength Y_T/MPa	40^b
Transverse compressive strength Y_C/MPa	145^b
Shear strength S₁₂, S₂₃, S₁₃/MPa	73^b
Out-of-plane tensile strength Z_T/MPa	40^b
Note: Superscripts ‘a’ and ‘b’ represent the data from experimental tests and research literature[13], respectively.

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表 3 纤维增强树脂复合材料失效准则^[16-17]

Table 3. Failure criteria of fiber reinforced resin composite^[16-17]

Failure mode	Failure criterion
Fiber tensile (${\varepsilon _{11}} > 0$)	$F_{ {\rm{ft} }}^2 = {\left( {\dfrac{ { {\varepsilon _{11} } } }{ {X_{\rm{T} }^\varepsilon } } } \right)^2} + {\left( {\dfrac{ { {\varepsilon _{12} } } }{ {S_{12}^\varepsilon } } } \right)^2} + {\left( {\dfrac{ { {\varepsilon _{13} } } }{ {S_{13}^\varepsilon } } } \right)^2}$
Fiber compression (${\varepsilon _{11}} \leqslant 0$)	$F_{{\rm{fc}}}^2 = {\left( {\dfrac{{{\varepsilon _{11}}}}{{X_{\rm{C}}^{11}}}} \right)^2}$
Matrix tensile ($({\varepsilon _{22}} + {\varepsilon _{33}}) \geqslant 0$)	$F_{{\rm{mt}}}^2 = {\left( {\dfrac{{{\varepsilon _{11}} + {\varepsilon _{33}}}}{{Y_{\rm{T}}^\varepsilon }}} \right)^2} + \left( {\dfrac{1}{{S{{_{23}^\varepsilon }^2}}}} \right)\left( {{\varepsilon _{23}}^2 - \dfrac{{{E_{22}}{E_{33}}}}{{{G_{23}}^2}}{\varepsilon _{22}}{\varepsilon _{33}}} \right) + {\left( {\dfrac{{{\varepsilon _{12}}}}{{S_{12}^\varepsilon }}} \right)^2} + {\left( {\dfrac{{{\varepsilon _{13}}}}{{S_{13}^\varepsilon }}} \right)^2}$
Matrix compression ($({\varepsilon _{22}} + {\varepsilon _{33}}) < 0$)	$\begin{array}{l} F_{ {\rm{mc} } }^2 = {\left( {\dfrac{ { {E_{22} }{\varepsilon _{22} } + {E_{33} }{\varepsilon _{33} } } }{ {2{G_{12} }S_{12}^\varepsilon } } } \right)^2} + \left( {\dfrac{ { {\varepsilon _{22} } + {\varepsilon _{33} } } }{ {Y{ {_{\rm{C} }^\varepsilon }^2} } } } \right)\left[ { { {\left( {\dfrac{ { {E_{22} }Y_{\rm{C}}^\varepsilon } }{ {2{G_{12} }S_{12}^\varepsilon } } } \right)}^2} - 1} \right] +\\ \quad\quad\dfrac{1}{ {S{ {_{23}^\varepsilon }^2} } }\left( { {\varepsilon _{23} }^2 - \dfrac{ { {E_{22} }{E_{33} } } }{ { {G_{23} }^2} }{\varepsilon _{22} }{\varepsilon _{33} } } \right) + {\left( {\dfrac{ { {\varepsilon _{12} } } }{ {S_{12}^\varepsilon } } } \right)^2} + {\left( {\dfrac{ { {\varepsilon _{13} } } }{ {S_{13}^\varepsilon } } } \right)^2} \\ \end{array}$
Delamination failure (${\varepsilon _{33}} \geqslant 0$)	$F_{{\rm{ld}}}^2 = {\left( {\dfrac{{{\varepsilon _{33}}}}{{Z_{\rm{T}}^\varepsilon }}} \right)^2} + {\left( {\dfrac{{{\varepsilon _{13}}}}{{S_{13}^\varepsilon }}} \right)^2} + {\left( {\dfrac{{{\varepsilon _{23}}}}{{S_{23}^\varepsilon }}} \right)^2}$
Notes: $X_{\rm{T}}^\varepsilon $—Longitudinal tensile strength strain; $X_{\rm{C}}^\varepsilon $—Longitudinal compressive strength strain; $Y_{\rm{T}}^\varepsilon $—Transverse tensile strength strain; $Y_{\rm{C}}^\varepsilon $—Transverse compressive strength strain; $S_{12}^\varepsilon $, $S_{13}^\varepsilon $, $S_{23}^\varepsilon $—Shear strain in the corresponding directions; $Z_{\rm{T}}^\varepsilon $—Out-of-plane tensile strength strain.

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表 4 界面粘接单元的材料属性^[24]

Table 4. Mechanical properties of cohesive element^[24]

Elastic property		Damage initiation			Damage evolution
E/GPa	G/GPa	N_max/MPa	S_max/MPa	T_max/MPa	G_ⅠC/(J·m⁻²)	G_ⅡC/(J·m⁻²)	G_ⅢC/(J·m⁻²)
2	0.75	65	38	38	2	4	4
Notes: E—Elastic modulus; G—Shear modulus; N_max, S_max, T_max—Traction in tension, shear 1 and shear 2, respectively; G_ⅠC, G_ⅡC, G_ⅢC—Fracture energy mode Ⅰ, Ⅱ and Ⅲ, respectively.

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表 5 2024-T3铝合金的各向同性硬化数据^[25]

Table 5. Isotropic hardening data of aluminum 2024-T3^[25]

Yield stress/MPa	300	320	340	355	375	390	410	430	450	470	484
Plastic strain/%	0	0.16	0.047	0.119	0.449	1.036	2.13	3.439	5.133	8.0	14.71

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表 6 含孔GF/EP复合材料-铝合金层板的损伤演化

Table 6. Damage evolution of GF/EP composite-aluminum alloy laminates with an open-hole

Open-hole diameter D	Fiber and matrix tensile damage evolution
2 mm	Increment step	144 722	153 859	164 658	182 922
2 mm
4 mm	Increment step	115 583	152 266	157 353	170 045
4 mm
6 mm	Increment step	112 855	132 492	144 664	151 741
6 mm
8 mm	Increment step	71 256	83 994	95 396	127 229
8 mm
10 mm	Increment step	56 025	64 276	75 626	115 428
10 mm

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