摘要
对于复合材料加筋层合板结构提出了一个逐步破坏的分析模型，它包含结构总体变形的几何非线性分析和结构内部材料局部损伤破坏的分析及其两者的相互作用。基于这一模型采用非线性有限元分析方法，研究了在压剪载荷作用下层合板结构的屈曲、后屈曲路径和破坏时极限载荷。
The paper presents a model to analysis the failure process of laminated composite plates and shells. Large deformation, local failure of material and their interaction are considered in the model. Based on the model and the finite element method, the buckling load, the postbuckling path and the catastrophic failure load of laminated composite plates and stiffened composite plates subjected to inplane loading were analysed.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1995年第1期118-122,共5页
Acta Aeronautica et Astronautica Sinica
关键词
复合材料
屈曲
层合加筋板
composite materials, ribs(supports), buckling, damage
