铺层和尺寸对含孔复材层板拉伸性能的影响  

Effect of ply and dimension on tensile properties of composite laminates with holes

作　　者：杨钧超 邹鹏 邓凡臣[1] 柴亚南[1] 熊美蓉 YANG Jun-chao;ZOU Peng;DENG Fan-chen;CHAI Ya-nan;XIONG Mei-rong(Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue,Aircraft Strength Research Institute of China,Xi'an 710065,China;COMAC Beijing Aeronautical Science&Technology Research Institute,Beijing 102211,China)

机构地区：[1]中国飞机强度研究所全尺寸飞机结构静力/疲劳航空科技重点实验室,西安710065 [2]中国商飞北京民用飞机技术研究中心,北京102211

出　　处：《复合材料科学与工程》2021年第11期5-11,共7页Composites Science and Engineering

基　　金：民机科研项目(MJ-2015-F-038);航空科学基金(2018ZE23011);国家自然科学基金(52005458)。

摘　　要：基于断裂面失效理论,建立了含孔复材层板渐进损伤数值分析模型。纤维失效后将损伤区的刚度直接折减为原来的0.01%;纤维间失效后基于能量释放率对损伤区的材料性能进行线性软化;同时,模型还考虑了剪切非线性效应对失效分析的影响。随后,模拟了不同孔径、铺层的含孔复合材料层合板的拉伸失效过程,并通过物理试验进行了验证。验证结果显示计算误差小于10%,且预测的失效模式与试验结果一致。最后,讨论了铺层、结构尺寸对含孔层合板破坏模式和强度的影响。同一孔径下,不同铺层的层合板破坏模式相近;同一铺层下,孔径与宽度比一定时,拉伸强度随孔径的增大而迅速减小。Based on the failure theory of fracture surface,a numerical model for progressive damage analysis of composite laminates with holes was established.After the failure of the fiber,the stiffness of the damaged area was directly reduced to 0.01%of the original value.After inter-fiber failure,the material properties in the damaged zone were softened linearly based on energy release rate.The effect of shear non-linearity on failure analysis was also considered in the model.Subsequently,the tensile failure process of composite laminates with different diameters and layers was simulated,and verified by physical tests.The results show that the calculation error is less than 10%,and the predicted failure mode is consistent with the test.Finally,the effects of layers and structure size on the failure mode and strength of laminates with holes were discussed.Under the same aperture,the failure modes of laminates with different layers are similar.Under the same layers,when the ratio of hole diameter to width is constant,the tensile strength decreases rapidly as the hole diameter increases.

关 键 词：复合材料 层合板 铺层 尺寸 拉伸强度 失效模式 

分 类 号：TB332[一般工业技术—材料科学与工程]