Performance Research of Asymmetric Variable Thickness Composite Laminate Under Compressive Load
俞晓楠 1许希武 1郭树祥 1冯浩凌1
扫码查看
点击上方二维码区域，可以放大扫码查看
作者信息
1. 南京航空航天大学机械结构力学及控制国家重点实验室,南京 210016
折叠
摘要
对非对称结构形式的变厚度复合材料层合板在准静态压缩载荷下的失效机理进行了试验和数值研究.在ABAQUS/Explicit中建立全新的三维有限元模型(Finite element model,FEM),其中Hashin准则用于复合材料层合板渐进失效分析,内聚力建模用于模拟分层的萌生和扩展.根据试验得到的应变数据分析,不连续的中性轴使层合板中产生弯矩,这些弯矩与轴向压缩载荷相互耦合,共同作用在层合板上.有限元结果表明,在薄段和变厚度段的交界处存在明显的应力集中,且薄段的应力大于厚段的应力.在交界处,发生了分层以及纤维和基体的压缩损伤,这与试验的结果一致.FEM预测的极限荷载比试验测得的平均极限荷载小10.7%,证明了模型的可行性和合理性.
Abstract
This study conducts an experimental and numerical investigation of failure mechanisms of variable thickness composite laminates with asymmetric structural forms under quasi-static compressive loading.A new 3-D finite element model(FEM)in ABAQUS/Explicit is established,where the Hashin criterion is used for composite laminate progressive failure analysis,and cohesive interface modeling is employed to simulate delamination initiation and dynamic propagation.According to the strain data from the experiment,the discontinuous neutral axis causes bending moments in the laminate,which are coupled with the axial compression load and interact together on the laminate.The FEM results indicate that there is a significant stress concentration at the junction of the thin section and the variable thickness section,and the stresses in the thin section are greater than those in the thick section.Delamination damage and fiber-matrix damage occurs at the junction,which is consistent with the findings of the experiment.The ultimate load estimated by FEM is 10.7%less than the average ultimate load measured by the experiment,demonstrating the model's viability and rationality.
关键词
变厚度复合材料/有限元分析/界面层/渐进损伤演化/压缩失效
Key words
variable thickness composites/finite element analysis(FEA)/interface layer/progressive damage evolution/compression failure
维普
万方数据