复合材料加筋板轴压后屈曲及承载有限元分析  

Finite Element Analysis of Post-Buckling and BearingCapability of Composite Stiffened Plates under Axial Compression

作　　者：王维阳[1] 李伟[1] 曹奇凯[1] WANG Wei-yang;LI Wei;CAO Qi-kai(Shenyang Aircraft Design and Research Institute,Shenyang Liaoning 110035,China)

机构地区：[1]沈阳飞机设计研究所,辽宁沈阳110035

出　　处：《计算机仿真》2022年第5期474-479,共6页Computer Simulation

摘　　要：基于Mindlin板理论和拟协调层板单元理论构建了帽形复合材料加筋壁板层合板屈曲及后屈曲行为的有限元求解列式。采用Hoffman准则针对单层板的破坏效应进行描述。采用弧长法和基于渐近分析的路径转换技术定义了三种逐渐破坏状态,进一步确定了壁板的后屈曲承载能力。通过板梁结构的数值分析对本文层合板方法的有效性进行了验证。进一步针对典型的帽形长桁复合材料壁板结构屈曲及后屈曲行为进行了数值分析,预测了临界压力和后屈曲承载极限。方法的构建为复杂的长桁加筋结构板屈曲临界荷载预测及后屈曲承载能力预测提供了理论及软件技术基础,为进一步类似复杂加筋复合材料结构设计和优化提供了有效方法,可有效降低试验成本并提高设计效率。Based on the Mindlin plate theory and the quasi-conforming laminate element theory,a finite element solution formula for the buckling and post-buckling behavior of the hat-shaped composite stiffened panels was constructed.The Hoffman criterion was used to describe the effect of the failure of the single-layer plate.Three gradual failure states were defined by the arc length method and the path conversion technique based on asymptotic analysis,and the post-buckling bearing capacity of the wall panel was further determined.The validity of the method in this paper was verified by the numerical analysis of the plate-beam structure.Furthermore,the buckling and post-buckling behaviors of typical cap-shaped stiffened composite panel was analyzed numerically,and the critical pressure and post-buckling bearing limit were predicted.The construction of the method provides theoretical and technical foundation for the prediction of critical buckling load and post-buckling bearing capacity of complex composite panels.It provides an effective method for further structural design and optimization of similar complex reinforced composite materials,which can effectively reduce experimental costs and improve design efficiency.

关 键 词：帽形长桁 复合材料 后屈曲 数值模拟 有限元方法 

分 类 号：V214.41[航空宇航科学与技术—航空宇航推进理论与工程]