碳纤维增强树脂基复合材料层合板胶螺混合连接失效机制

刘礼平; 段科好; 徐卓; 冯振宇; 蔺越国; 郑亦媚; 宋肖肖

doi:10.13801/j.cnki.fhclxb.20220215.001

碳纤维增强树脂基复合材料层合板胶螺混合连接失效机制

doi: 10.13801/j.cnki.fhclxb.20220215.001

1.
中国民航大学　航空工程学院，天津 300300
2.
中国民航大学　安全科学与工程学院，天津 300300
3.
中国民航大学　中欧航空工程师学院，天津 300300

基金项目: 中央高校科研基本业务费(3122018D040)

详细信息

通讯作者:
刘礼平，博士，副教授，硕士生导师，研究方向为复合材料结构修理　E-mail: liuliping_tj@163.com

中图分类号: V260
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出版历程
- 收稿日期: 2021-12-10
- 修回日期: 2022-01-07
- 录用日期: 2022-01-18
- 网络出版日期: 2022-02-15
- 刊出日期: 2023-01-15

Failure mechanism of carbon fiber reinforced polymer bonded-bolted hybrid connection

1.
College of Aviation Engineering, Civil Aviation University of China, Tianjin 300300, China
2.
College of Safety Science and Engineering, Civil Aviation University of China, Tianjin 300300, China
3.
Sino-European Institute of Aviation Engineering, Civil Aviation University of China, Tianjin 300300, China

Funds: Fundamental Research Funds for the Central Universities (3122018D040)

摘要

摘要: 为研究碳纤维增强树脂基复合材料(CFRP)层合板单搭接双螺栓胶螺混合连接失效机制，采用基于断裂能断裂准则的连续渐进退化方式，仿真CFRP层合板刚度退化，采用基于能量的B-K准则仿真胶层的损伤演化，建立胶螺混合连接结构渐进损伤三维有限元模型，有限元模型预测的最大失效载荷与实验结果吻合较好。搭接长度L_a为影响胶螺混合接头刚度和强度的重要几何参数，螺栓的位置不会明显影响接头的刚度，粘结面积越大，强度越大。胶螺混合接头在拉伸载荷作用下，由于二次弯曲效应的影响，螺栓向左倾斜，搭接区域的胶层损伤起始于搭接区域胶层外侧，并由外侧向内部扩展到钉孔附近，当胶层损伤扩展到钉孔附近时，螺栓承载增加，胶层和螺栓共同承载，此时CFRP层合板开始出现损伤；最终，左侧钉孔处的上层合板和右侧钉孔处的下层合板产生分层损伤并发生断裂。
- 碳纤维增强树脂基复合材料(CFRP) /
- 胶螺混合连接 /
- 失效机制 /
- 有限元分析 /
- 二次弯曲效应
Abstract: In order to study the failure mechanism of the single-lap two-bolt bonded-bolted hybrid connection of carbon fiber reinforced polymer (CFRP) laminates, the continuous progressive degradation method based on fracture energy fracture criterion was used to simulate the stiffness degradation of CFRP laminates, and the B-K criterion based on energy was used to simulate the damage evolution of the adhesive layer. A three-dimensional finite element model of progressive damage of the bonded-bolted hybrid connection structure was established. The maximum failure load predicted by the finite element model is in good agreement with the experimental results. Lap length L_a is an important geometric parameter affecting the stiffness and strength of the bonded-bolted hybrid joint. The position of bolt will not significantly affect the stiffness of joint. The larger the bonding area, the greater the strength. Under the action of tensile load, the bolt of the bonded-bolted hybrid joint is inclined to the left due to the influence of the secondary bending effect. The adhesive layer damage in the overlap area starts from the outside of the adhesive layer in the overlap area and expands from the outside to the inside to the vicinity of the bolt hole. When the damage of the adhesive layer extends to the vicinity of the bolt hole, the load of the bolt increases, and the adhesive layer and the bolt bear the load together. At this time, the CFRP laminates begin to damage, and the upper composite plate at the left hole and the lower composite plate at the right hole produce delamination damage and fracture.
- carbon fiber reinforced polymer (CFRP) /
- bonded-bolted hybrid connection /
- failure mechanism /
- finite element analysis /
- secondary bending effect

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图 1 单搭接双螺栓胶螺混合接头示意图

Figure 1. Schematic diagram of single lap two-bolt bonded-bolted hybrid joint

L—Substrate length; W—Substrate width; t—Substrate thickness; t_a—Adhesive thickness; L_a—Overlap length; E—Bolt-edge distance; L_j—Inter-bolt distance; Ø—Diameter

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图 2 连续渐进损伤变量求解关系

Figure 2. Solution relationship of continuous progressive damage variable

$d_{ii}^{\text{T}} $—Damage variable; σ_ii—Stress; $ \varepsilon _{0,i}^{\text{T}} $—Element initial damage strain in tensile mode; $ \varepsilon _{{\text{f}},i}^{\text{T}} $—Element failure strain in tensile mode; ${\sigma ^{\text{T}}}$—Element initial damage stress in tensile mode

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图 3 复合材料层合板渐进损伤分析VUMAT流程图

Figure 3. VUMAT flow chart for progressive damage analysis of composite laminates

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图 4 单搭接双螺栓胶螺混合接头构型4载荷-位移曲线

Figure 4. Load-displacement curves of configuration 4 of single lap two-bolt bonded-bolted hybrid joint

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图 5 单搭接双螺栓胶螺混合接头5种构型的载荷-位移曲线

Figure 5. Load-displacement curves of five configurations of single lap two-bolt bonded-bolted hybrid joint

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图 6 单搭接双螺栓胶螺混合接头失效变形图

Figure 6. Failure deformation of single lap two-bolt bonded-bolted hybrid joint

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图 7 单搭接双螺栓胶螺混合接头钉孔处层合板基体失效图：(a)左侧钉孔；(b)右侧钉孔

Figure 7. Matrix failure diagram of laminate at bolt hole of single lap two-bolt bonded-bolted hybrid joint: (a) Left bolt hole; (b) Right bolt hole

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图 8 单搭接双螺栓胶螺混合接头胶层损伤扩展云图

Figure 8. Nephogram of damage expansion of adhesive layer of single lap two-bolt bonded-bolted hybrid joint

SDEG—Scalar stiffness degradation

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图 9 单搭接双螺栓胶螺混合接头左侧钉孔处上层合板基体和纤维损伤扩展云图

Figure 9. Matrix and fiber damage expansion nephogram of the upper laminate at the bolt hole on the left of single lap two-bolt bonded-bolted hybrid joint

SDV3—Damage state of matrix

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图 10 单搭接双螺栓胶螺混合接头二次弯曲变形和临界位置示意图

Figure 10. Diagram of secondary bending deformation and critical position of single-lap two-bolt bonded-bolted hybrid joint

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图 11 “螺栓A” 4个区域划分和受力分析

Figure 11. Four regions division and stress analysis of bolt A

F_c1—Magnitude of total force due to contact pressure (CFNM) for region C; F_d1—CFNM for region D; F_e1—CFNM for region E; F_f1—CFNM for region F

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图 12 螺栓四个不同区域法向接触力(CFNM)-时间曲线

Figure 12. Magnitude of total force due to contact pressure (CFNM)-time curves of four different regions of bolt

F—Tensile load; F_c—Resultant CFNM for regionC; F_d—Resultant CFNM for regionD; F_e—Resultant CFNM for regionE; F_f—Resultant CFNM for regionF

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图 13 单搭接双螺栓胶螺混合接头纵向断面宏观破坏形貌^[17]

Figure 13. Macroscopic failure morphology of longitudinal cross-section of single-lap two-bolt bonded-bolted hybrid joint^[17]

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表 1 单搭接双螺栓胶螺混合接头几何尺寸

Table 1. Geometry of single lap two-bolt bonded-bolted hybrid joint mm

Parameter	Overlap length L_a	Bolt-edge distance E	Inter-bolt distance L_j
Configuration 1	50	14	22
Configuration 2	50	8	34
Configuration 3	62	14	34
Configuration 4	62	8	46
Configuration 5	74	20	34

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表 2 Cycom 5320碳纤维增强树脂基复合材料 (CFRP) 层合板材料参数

Table 2. Material parameters of Cycom 5320 carbon fiber reinforced polymer (CFRP) laminate

Property	Value
E₁₁/GPa	141
E₂₂=E₃₃/GPa	9.7
G₁₂=G₁₃/GPa	5.2
G₂₃/GPa	3.4
ν₁₂=ν₁₃	0.34
ν₂₃	0.44
X_T/MPa	2703
X_C/MPa	1737
Y_T=Z_T/MPa	81
Y_C=Z_C/MPa	312
S₁₂=S₁₃=S₂₃/MPa	57
Notes: E_ii—Young’s modulus; G_ij—Shear modulus; ν_ij—Possion ratio; X_T and X_C—Tension and compressive strength on the direction 1; Y_T and Y_C—Tension and compressive strength on the direction 2; Z_T and Z_C—Tension and compressive strength on the direction 3; S_ij—Shear strength; i, j=1, 2, 3.

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表 3 Hysol EA9361胶层材料参数

Table 3. Material parameters of Hysol EA9361 adhesive layer

Property	Value
E_nn/GPa	5.14
E_ss=E_tt/GPa	1.74
σ_0,n/MPa	14.6
σ_0,s/MPa	27.5
σ_0,t/MPa	27.5
G_c,n= G_c,s= G_c,t/(N·mm⁻¹)	1.0
Notes: E_ii—Young’s modulus; σ_0,i—Initial damage stress of the cohesive element; G_c,i—Fracture toughness of crack; i=n, s, t.

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表 4 单搭接双螺栓胶螺混合接头最大失效载荷

Table 4. Ultimate failure load of single lap two-bolt bonded-bolted hybrid joint

Parameter	Experiment/kN	FEM/kN	Difference/%
Configuration 1	26.71±1.43	28.11	5.24
Configuration 2	29.46±1.21	28.90	1.90
Configuration 3	30.97±0.49	30.65	1.03
Configuration 4	30.75±1.65	31.80	3.41
Configuration 5	36.88±3.39	36.57	0.84

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