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铺层角度对CFRP多向层板Ⅱ型分层扩展行为的影响

张寒松 龚愉 林文娟 张建宇 赵丽滨

张寒松, 龚愉, 林文娟, 等. 铺层角度对CFRP多向层板Ⅱ型分层扩展行为的影响[J]. 复合材料学报, 2022, 39(9): 1-11 doi: 10.13801/j.cnki.fhclxb.20220329.001
引用本文: 张寒松, 龚愉, 林文娟, 等. 铺层角度对CFRP多向层板Ⅱ型分层扩展行为的影响[J]. 复合材料学报, 2022, 39(9): 1-11 doi: 10.13801/j.cnki.fhclxb.20220329.001
Hansong ZHANG, Yu GONG, Wenjuan LIN, Jianyu ZHANG, Libin ZHAO. Effect of ply angle on mode II delamination propagation behavior of CFRP multidirectional laminates[J]. Acta Materiae Compositae Sinica, 2022, 39(9): 1-11. doi: 10.13801/j.cnki.fhclxb.20220329.001
Citation: Hansong ZHANG, Yu GONG, Wenjuan LIN, Jianyu ZHANG, Libin ZHAO. Effect of ply angle on mode II delamination propagation behavior of CFRP multidirectional laminates[J]. Acta Materiae Compositae Sinica, 2022, 39(9): 1-11. doi: 10.13801/j.cnki.fhclxb.20220329.001

铺层角度对CFRP多向层板Ⅱ型分层扩展行为的影响

doi: 10.13801/j.cnki.fhclxb.20220329.001
基金项目: 国家自然科学基金(12172067;11902054;12072052;12072005;11872131;U1864208);中央高校基本科研业务费(2020CDJGFHK009);重庆英才青年拔尖人才计划(CQYC2021059215)
详细信息
    通讯作者:

    龚愉,博士,副教授,硕士生导师,研究方向为复合材料力学  E-mail: gongyu@cqu.edu.cn

  • 中图分类号: TB332

Effect of ply angle on mode II delamination propagation behavior of CFRP multidirectional laminates

  • 摘要: 碳纤维增强树脂复合材料(CFRP)因其良好的力学性能被逐渐应用于飞机主承力结构中。分层是复合材料层板最常见的损伤形式之一,也是飞机复合材料结构损伤容限设计与分析所关注的焦点问题。对于II型分层,现有研究主要针对单向层板展开,而工程实际中应用较多的是多向层板,对II型分层的铺层角度影响缺乏深入认识。为此,采用试验和数值方法开展了相关研究。首先设计了3种工程实际中常用界面(0°/5°、45°/−45°和90°/90°)的T700/QY9511碳纤维/双马来酰亚胺树脂基复合材料层板,所设计铺层可降低耦合作用并确保II型主导的分层扩展。采用端部开口弯曲装置开展了II型分层试验并测得了断裂韧性。结果表明:铺层角度对断裂韧性和分层失效行为影响显著。采用控制变量法建立了内聚力关键参数模型,在此基础上实现了多向层板II型分层扩展行为的模拟,预测的载荷-位移曲线响应与试验结果吻合很好,说明了有限元模型的有效性。有限元结果表明,基体损伤做功表现出随铺层角度增加而增加的趋势。为揭示基体损伤做功与分层前缘损伤区大小之间的关系,利用用户自定义子程序,模拟了不同界面试样的分层前缘损伤区域。

     

  • 图  1  ENF试样形式与几何尺寸

    Figure  1.  ENF specimen and geometrical dimensions

    B—Specimen width; a0—Length of the initial pre-crack; L—Half of the span; h—Half of the specimen thickness

    图  2  ENF试验的三点弯加载方案示意图

    Figure  2.  Sketch of the three-point bending in ENF test

    图  3  T700/QY9511碳纤维/双马来酰亚胺树脂基复合材料多向层板ENF试样载荷-位移曲线

    Figure  3.  Load-displacement curves of T700/QY9511 carbon fiber reinforced bismaleimide composite multidirectional laminate ENF specimens

    图  4  T700/QY9511多向层板ENF试样分层路径图片

    Figure  4.  Pictures of crack path of T700/QY9511 multidirectional laminate ENF specimens

    图  5  II型分层双线性本构关系

    Figure  5.  Bilinear constitutive law of mode II delamination

    P—Load; σ—Stress; δ—Displacement; K0—Interfacial stiffness; d—Damage variable; σ0II—Interfacial strength; δ0II—Displacement when damage initiation occurs; δfII—Displacement when the interface just loses its bearing capacity

    图  6  T700/QY9511多向层板ENF试样的有限元模型 (a)、预制裂尖 (b) 和变形模拟结果 (c)

    Figure  6.  Numerical model (a), pre-crack tip (b) and simulated results (c) of T700/QY9511 multidirectional laminate ENF specimen

    图  7  0°/5°铺层角度T700/QY9511多向层板试样内聚力单元参数的确定

    Figure  7.  Determination of cohesive element parameters of T700/QY9511 multidirectional laminates with 0°/5° interface

    图  8  不同界面强度下T700/QY9511多向层板的模拟结果

    Figure  8.  Simulated results of T700/QY9511 multidirectional laminates under different interfacial strengths

    图  9  T700/QY9511多向层板内聚力单元的Mises应力云图

    Figure  9.  Mises stress in cohesive elements of T700/QY9511 multidirectional laminates

    图  10  T700/QY9511多向层板II型分层过程能量消耗情况示意图

    Figure  10.  Schematic diagram of energy consumption in mode II delamination process of T700/QY9511 multidirectional laminates

    图  11  基于奇异元的T700/QY9511多向层板数值模型:(a) ENF有限元模型;(b) 裂尖网格;(c) 三维奇异元示意图

    Figure  11.  Numerical model of T700/QY9511 multidirectional laminates based on singular element: (a) ENF FE model; (b) Mesh around crack tip; (c) Sketch of 3D singular element

    图  12  T700/QY9511多向层板裂纹尖端应力状态

    Figure  12.  Stress status of crack tip in T700/QY9511 multidirectional laminates

    σx—Stress along the x direction; τxz—Shear stress in the x-o-z plane; θ—Ply angle adjacent to the interface

    图  13  不同界面T700/QY9511多向层板试样的分层前缘损伤区

    Figure  13.  Damage area around crack tip of T700/QY9511 multidirectional laminates with different interfaces

    表  1  复合材料多向层板端部开口弯曲(ENF)试样铺层信息

    Table  1.   Stacking sequences of the composite multidirectional laminate end-notched flexure (ENF) specimens

    No.Ply-upDelamination interfaceDcBtFlexural modulus Efx
    ENF-116//(5°/−5°/0°6)S0°/5°0.00960.0063129.2947
    ENF-2(45°/−45°/0°6)S//(−45°/45°/0°6)S45°/−45°0.15270.030867.9749
    ENF-3(90°/0°/90°/0°5)S//(90°/0°/90°/0°5)S90°/90°0.0020≈069.6301
    Notes: Dc and Bt—Dimensionless parameters; //—Location of the prefabricated crack introduced during manufacturing.
    下载: 导出CSV

    表  2  T700/QY9511多向层板ENF试样的挠度和临界载荷值

    Table  2.   Deflection and critical load values of T700/QY9511 multidirectional laminate ENF specimens

    Delamination interfaceNo.Width/
    mm
    Deflection/
    mm
    Critical
    load/N
    0°/5°ENF-1-125.011.901119
    ENF-1-225.012.271235
    ENF-1-325.012.161067
    45°/−45°ENF-2-124.942.591016
    ENF-2-224.982.88915
    ENF-2-325.002.531038
    90°/90°ENF-3-124.992.23811
    ENF-3-225.042.40727
    ENF-3-325.072.17774
    下载: 导出CSV

    表  3  不同分层界面T700/QY9511多向层板ENF试样的断裂韧性试验值

    Table  3.   Fracture toughness values of T700/QY9511 multidirectional laminate ENF specimens with different interfaces

    Delamination interfaceNo.GⅡC/(J·m−2)Average value/( J·m−2)Standard deviation/(J·m−2)Cv/%
    0°/5° ENF-1-1 805.22 912.94 133.16 14.59
    ENF-1-2 1061.83
    ENF-1-3 871.77
    45°/−45° ENF-2-1 1000.79 997.57 3.31 0.33
    ENF-2-2 997.77
    ENF-2-3 994.17
    90°/90° ENF-3-1 686.81 660.12 26.51 4.02
    ENF-3-2 659.78
    ENF-3-3 633.77
    Notes: GⅡCMode II strain energy release rate; Cv—Coefficient of variation.
    下载: 导出CSV

    表  4  不同界面强度下T700/QY9511多向层板临界载荷模拟值与试验均值对比

    Table  4.   Simulated and experimental values of critical load of T700/QY9511 multidirectional laminates under various interfacial strengths

    Delamination interfaceInterfacial strength/MPaSimulated result of critical load/NAverage test value/NRelative error/%
    0°/5° 30 990.3 1140.3 −13.2
    40 1113.4 −2.4
    50 1154.4 1.2
    45°/−45° 50 881.6 989.7 −10.9
    60 1012.5 2.3
    70 1165.9 17.8
    90°/90° 35 701.7 770.7 −9.0
    45 781.3 1.4
    50 870.8 13.0
    下载: 导出CSV

    表  5  T700/QY9511多向层板分层起始时刻裂尖应变能释放率(SERR)分量

    Table  5.   Strain energy release rate (SERR) components of crack tip at the delamination initiation moment of T700/QY9511 multidirectional laminates

    Delamination
    interface
    GI/(J·m−2)GII/( J·m−2)GIII/( J·m−2)GII/
    (GI+GII+GIII)
    0°/5°0.26894.081.151.00
    45°/-45°0.68950.5228.320.97
    90°/90°0.06608.031.091.00
    Notes: GI—Mode I strain energy release rate; GII—Mode II strain energy release rate; GIII—Mode III strain energy release rate.
    下载: 导出CSV
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  • 收稿日期:  2022-01-25
  • 录用日期:  2022-03-18
  • 修回日期:  2022-03-09
  • 网络出版日期:  2022-03-31
  • 刊出日期:  2022-09-15

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