剪切载荷下复合材料开口腹板强度及损伤预测

Strength and Damage Prediction of Composite Panel with a Cutout under Shear Load

采用Hashin损伤初始准则和基于能量耗散的损伤演化准则,结合有限元法对某型直升机涵道大垂尾前缘锥体复合材料开口腹板的损伤失效过程及剪切承载能力进行预测。并将数值计算结果与剪切试验结果进行对比分析,结果表明数值预测的剪切屈曲变形、损伤位置、模式及形貌的预测结果与实验结果吻合良好。数值预测的极限剪切载荷和失效位移的误差分别为2.06%和-2.05%;该建模和分析策略可为渐进损伤方法在复合材料直升机结构的强度分析中的应用提供参考。

The damage failure progress and shear capacity of composite panel with large cutout on the fenestron of a helicopter are predicted by using the Hashin damage initial criterion and energy dissipation based damage evolution criterion combined with the finite element method. The prediction results of the buckling deformation, damage location, mode and morphology are good agreement with the experimental results. The results show that the prediction errors of the ultimate shear load and failure displacement are 2.06% and-2.05% respectively. The modelling and analysis strategy can provide engineering reference for the use of progressive damage analysis in the strength design of composite helicopter structures.