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碳纤维/环氧树脂复合材料L型接头拉伸失效机制

张琪 蔡登安 余章杰 戴征征 吴大可 周光明

张琪, 蔡登安, 余章杰, 等. 碳纤维/环氧树脂复合材料L型接头拉伸失效机制[J]. 复合材料学报, 2022, 40(0): 1-11
引用本文: 张琪, 蔡登安, 余章杰, 等. 碳纤维/环氧树脂复合材料L型接头拉伸失效机制[J]. 复合材料学报, 2022, 40(0): 1-11
Qi ZHANG, Deng’an CAI, Zhangjie YU, Zhengzheng DAI, Dake WU, Guangming ZHOU. Tensile failure mechanism of carbon fiber/epoxy composite L-joints[J]. Acta Materiae Compositae Sinica.
Citation: Qi ZHANG, Deng’an CAI, Zhangjie YU, Zhengzheng DAI, Dake WU, Guangming ZHOU. Tensile failure mechanism of carbon fiber/epoxy composite L-joints[J]. Acta Materiae Compositae Sinica.

碳纤维/环氧树脂复合材料L型接头拉伸失效机制

基金项目: 国家自然科学基金(52005256);江苏省基础研究计划(自然科学基金)资助项目(BK20190394);江苏省博士后科研资助计划项目(2020Z437);中央高校基本科研业务费专项资金资助(NS2019001);江苏高校优势学科建设工程资助项目(PAPD)
详细信息
    通讯作者:

    周光明,博士,教授,博士生导师,研究方向为先进复合材料结构设计及工程问题的计算机建模 E-mail: zhougm@nuaa.edu.cn

  • 中图分类号: TB332

Tensile failure mechanism of carbon fiber/epoxy composite L-joints

  • 摘要: 设计了单L型(LS)及双L型(LD)两种重量相近的L型接头。采用试验与数值模拟相结合的方式对两种接头的拉伸失效机制进行了研究。通过自行设计的试验夹具在MTS试验机上将两种L型接头准静态加载至破坏,分析其破坏机理及应变分布。研究发现,两种L型接头存在不同的失效机制,在破坏阶段单L型接头表现出更好的延展性。单L型接头加载至峰值载荷时,在靠近加载侧的内侧螺栓孔附近首先出现破坏,随后损伤向外侧螺栓孔附近扩展,直至完全失效。双L型接头加载至峰值载荷的50%左右时,L型框体和L型片之间的胶膜首先发生破坏,随后载荷继续增加至峰值载荷时,L型框螺栓孔附近发生破坏,损伤向框体边缘扩展,载荷大幅下降。此外,两种接头的应变随载荷的增加存在不同的变化趋势。采用一种新型复合材料初始失效准则及刚度折减方法,编写用户自定义子程序(UMAT),结合内聚区模型建立复合材料L型接头的渐进损伤模型。基于ABAQUS软件进行计算,得到接头的预测失效载荷及破坏形式。结果表明:有限元分析所得复合材料L型接头的损伤位置及失效模式与试验吻合,预测载荷与试验值相差较小,证明了有限元模型的适用性。

     

  • 图  1  单L型接头(LS)几何尺寸 (单位:mm)

    Figure  1.  Geometry configuration of single L-joint (LS) (Unit: mm)

    图  2  双L型接头(LD)几何尺寸 (单位:mm)

    Figure  2.  Geometry configuration of double L-joint (LD) (Unit: mm)

    图  3  碳纤维/环氧树脂复合材料单L型及双L型接头试件加载示意图

    Figure  3.  Loading schematic diagram of carbon fiber/epoxy composite single L-joint and double L-joint

    图  4  L型接头试验机加载图

    Figure  4.  L-joints on test machine

    图  5  单L型及双L型接头应变花位置示意图

    Figure  5.  Schematic of strain rosette positions of single L-joint and double L-joint

    图  6  单L型(LS1~LS3)及双L型(LD1~LD3)接头载荷-位移曲线

    Figure  6.  Load-displacement curves of single L-joints (LS1-LS3) and double L-joint (LD1-LD3)

    图  7  L型框螺栓附近破坏情况

    Figure  7.  Damage near the bolts of the L-frame

    图  8  L型框侧面拐角位置破坏情况

    Figure  8.  Damage of the side corners of the L-frame

    图  9  LS1和LD1的应变-载荷曲线:(a) L型框正面:面A;(b) LS1中L型框背面,LD1中L型片正面:面B;(c) L型框底面:面C;(d) L型框侧面:面D

    Figure  9.  Strain-load curves of LS1 and LD1: (a) Front of L frame: surface A; (b) Back of the L frame: surface B; (c) Bottom of the L frame: surface C; (d) Side of the L frame: surface D

    图  10  双L型接头11~18号测点各方向应变-载荷曲线:(a) L型片底部:11号、12号测点;(b) L型片螺栓附近:13号、14号、15号;(c) L型框螺栓附近:16号、17号、18号

    Figure  10.  Strain-load curves in each direction at measuring points 11-18 for double L-joint: (a) Bottom of L-piece: No.11 and No.12; (b) Near bolts of the L-piece: No.13, No.14 and No.15 ; (C) Near bolts of the L-frame: No.16, No.17 and No.18

    图  11  碳纤维/环氧树脂复合材料L型接头有限元模型约束加载示意图

    Figure  11.  Schematic of constraint and load for finite element model of carbon fiber/epoxy composite L-joint

    图  12  单L型接头仿真损伤云图

    Figure  12.  Simulated damage diagram of a single L-joint

    图  13  双L型接头仿真损伤云图

    Figure  13.  Simulated damage diagram of a double L-joint

    图  14  各载荷阶段双L型接头胶层损伤云图:(a) 1.51 kN; (b) 3.26 kN (c) 5.17 kN (d) 7.72 kN

    Figure  14.  Simulated diagram of adhesive layer damage of double L-joints in each load stage: (a) 1.51 kN; (b) 3.26 kN (c) 5.17 kN (d) 7.72 kN

    表  1  碳纤维/环氧树脂复合材料的性能参数

    Table  1.   Material properties of carbon fiber/epoxy composite

    Parameters${E_x} = {E_y}$
    /GPa
    ${E_z}$
    /GPa
    ${\mu _{xy}}$${\mu _{xz}} = {\mu _{yz}}$${G_{xy}}$
    /GPa
    ${G_{xz}} = {G_{yz}}$
    /GPa
    Material Properties57.715*0.070.27*9.76*
    Fracture Parameters${X_{\text{T}}} = {Y_{\text{T}}}$
    /MPa
    ${Z_{\text{T}}}$
    /MPa
    ${X_{\text{C}}} = {Y_{\text{C}}}$
    /MPa
    ${Z_{\text{C}}}$
    /MPa
    ${S_{xy}}$
    /MPa
    ${S_{xz}} = {S_{yz}}$
    /MPa
    Material Properties609.750*533.6150*141.770*
    Notes: *Material data were provided by the manufacture, Avic Aviation High-tech Co. LTD. The rest data were measured by experiment on the laminates; ${E_x}, {E_y}, {E_z}$—Elastic modulus in direction of x, y, z; ${X_{\text{T}}}$,${Y_{\text{T}}}$,${Z_{\text{T}}}$—Tensile strength in the three directions above, respectively; ${X_{\text{C}}}$,${Y_{\text{C}}}$,${Z_{\text{C}}}$—Compress strength in the three directions above, respectively; ${\mu _{ij}}$,${G_{ij}}$,${S_{ij}}$( i, j = x, y, z )—Poisson’s ratio, shear modulus and shear strength for x-y, x-z, y-z plane, respectively.
    下载: 导出CSV

    表  2  碳纤维/环氧树脂复合材料L型接头拉伸试验结果

    Table  2.   Tensile load test results of carbon fiber/epoxy composite L-joint

    Specimen numberFailure load/
    kN
    Average load/
    kN
    Coefficient of variation /%
    LS114.22514.1094.296
    LS213.316
    LS314.787
    LD114.30514.2151.095
    LD214.344
    LD313.996
    下载: 导出CSV

    表  3  碳纤维/环氧树脂复合材料接头性能退化方式

    Table  3.   Degradation modes of carbon fiber/epoxy composite joint

    DirectionCriterionMaterial
    constants
    to degrade
    Stiffness
    degradation
    ratio
    xEq. (1)$\begin{gathered} {E_x},{\mu _{xy}},{\mu _{xz}}, \hfill \\ {G_{xy}},{G_{xz}} \hfill \\ \end{gathered} $0.4407
    Eqs. (2) and (3)0.001
    yEq. (4)$\begin{gathered} {E_y},{\mu _{xy}},{\mu _{yz}}, \hfill \\ {G_{xy}},{G_{yz}} \hfill \\ \end{gathered} $0.4407
    Eqs. (5) and (6)0.001
    zEqs. (7) and (8)$\begin{gathered} {E_z},{\mu _{xz}},{\mu _{yz}}, \hfill \\ {G_{xz}},{G_{yz}} \hfill \\ \end{gathered} $0.001
    下载: 导出CSV

    表  4  J-116B结构胶材料属性[25]

    Table  4.   Material properties of J-116B adhesive[25]

    ParameterStiffnessNormal strength
    $t_{\text{n}}^{\text{o}}$/ MPa
    Shear strength
    $t_{\text{s}}^{\text{o}} = t_{\text{t}}^{\text{o}}$/ MPa
    Fracture energy
    ${G^{\text{C}}}$/${\text{(J}} \cdot {{\text{m}}^{{{ - 2}}}})$
    $E/{E_{{\text{nn}}}}$/${\text{(MPa}} \cdot {\text{m}}{{\text{m}}^{{{ - 1}}}})$${G_1}/{E_{{\text{ss}}}} = {G_2}/{E_{{\text{tt}}}}$/${\text{(MPa}} \cdot {\text{m}}{{\text{m}}^{{{ - 1}}}})$
    Value100030020302
    Notes:$E/{E_{{\text{nn}}}}$,${G_1}/{E_{{\text{ss}}}}$,${G_2}/{E_{{\text{tt}}}}$—Interface stiffness for three directions, respectively; $t_{\text{n}}^{\text{o}}$,$t_{\text{s}}^{\text{o}}$,$t_{\text{t}}^{\text{o}}$—Interface strength for three directions, respectively.
    下载: 导出CSV

    表  5  碳纤维/环氧树脂复合材料L型接头部分测点应变仿真值与试验值对比

    Table  5.   Comparison of simulation and test values of some strain gauges on carbon fiber/epoxy composite L-joint

    Strain gauge numberSingle L-joint at 12 kNDouble L-joint at 6 kN
    Simulation
    value/10−6
    Test
    value/10−6
    Simulation
    value/10−6
    Test
    value/10−6
    51321167553110
    6132111435330
    11−1270−1446387476
    12−1270−1173387393
    133110447128222810
    14391533133003703
    153110130828223175
    下载: 导出CSV
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  • 收稿日期:  2021-12-31
  • 录用日期:  2022-03-05
  • 修回日期:  2022-02-23
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