碳纤维开孔层合板拉伸载荷下的失效分析

Failure Analysis of Carbon Fiber Open-Hole Laminates Under Tensile Load

【目的】研究开孔碳纤维复合材料层合板在拉伸载荷下的失效行为,并确定铺层顺序、铺层角度对极限载荷的影响。【方法】通过Abaqus有限元软件和Hashin失效准则,建立壳单元在拉伸载荷下的失效模型,利用该失效模型进行数值模拟分析。【结果】0°层失效首先发生在孔边,随着孔边失效区域的不断扩大,呈现由X形向沙漏形转变的趋势;在达到极限载荷前,承载力与位移成正比,之后承载力迅速下降,层合板将迅速失效;铺层顺序对层合板的强度影响不大,铺层角度对层合板的极限载荷影响较大。在一定范围内增加±45°铺层的数量,不仅可以延缓层合板的失效,而且可以提高极限载荷值。【结论】研究结果对开孔碳纤维复合材料层合板的实际应用具有指导作用。

[Purposes]The failure behavior of open-hole carbon fiber composite laminates under tensile load was studied,and the influence of ply sequence and ply angle on the ultimate load was discussed.[Methods]The failure model of shell element under tensile load was established by Abaqus finite element software and Hashin failure criterion.The failure model was used for numerical simulation analysis and discussion.[Findings]The failure of 0°layer first occurs at the edge of the hole.With the continuous expansion of the failure area at the edge of the hole,it shows a transition from X shape to hourglass shape.Before reaching the ultimate load,the bearing capacity is proportional to the displacement,and as the bearing capacity decreases rapidly,the laminate will fail rapidly.The stacking sequence has little effect on the strength of the laminates,and the stacking angle has a great influence on the ultimate load of the laminates.Increasing the number of positive and negative 45°layers within a certain range can not only delay the failure of the laminate,but also increase its ultimate load value.[Conclusions]The research results have a guiding role in the practical application of perforated carbon fiber composite laminates.