Failure Analysis of Carbon Fiber Open-Hole Laminates Under Tensile Load
[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 ex-pansion of the failure area at the edge of the hole,it shows a transition from X shape to hourglass shape.Be-fore 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 lami-nates.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.
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万方数据
维普
