飞机复合材料加筋壁板结构屈曲和后屈曲研究  

The Investigation on Buckling and Post Buckling of Aircraft Composite Panel Structure

作　　者：张修路 黄文超[2] 方采文 李常有[3] ZHANG Xiu-lu;HUANG Wen-chao;Fang Cai-wen;LI Chang-you(Institute of Electrical Engineering,Shenyang City University,Shenyang Liaoning 110112,China;Engineering Research BU,AVIC SAC Commercial Aircraft Company Ltd.,Shenyang Liaoning 110000,China;Institute of Mechanical Engineering&Automation,Northeastern University,Shenyang Liaoning 110000,China)

机构地区：[1]沈阳城市学院机电工程学院,辽宁沈阳110112 [2]中航沈飞民用飞机有限责任公司工程研发事业部,辽宁沈阳110000 [3]东北大学机械工程与自动化学院,辽宁沈阳110000

出　　处：《计算机仿真》2020年第12期230-234,408,共6页Computer Simulation

基　　金：国家自然科学基金资助项目(51671065)。

摘　　要：对复合材料加筋壁板结构进行压缩稳定性试验和有限元仿真分析研究。首先,建立复合材料加筋壁板结构的有限元仿真模型,通过计算有限元仿真应变数据和试验应变数据之间的SAC(应变判定准则)值来验证仿真模型的准确性。然后,采用特征值分析法对结构进行屈曲分析,得到结构的屈曲模态、屈曲特征值以及屈曲载荷。接着,利用弧长法对结构进行后屈曲分析,得到结构的屈曲载荷、后屈曲承载路径以及破坏载荷。最后,对比研究两种分析方法计算值与试验分析值,验证了分析方法的正确性。探索出了加筋壁板结构屈曲与后屈曲的分析方法,对加筋壁板承载能力的研究有着指导借鉴作用。The compression test and finite element simulation were made to study the stability of stiffened composite panel.Firstly,the finite element model of stiffened composite panel was created by calculating the value of the Strain Assurance Criterion(SAC)of the finite element simulation and the test to verify the feasibility of the simulation model.Secondly,The buckling analysis was carried out by using eigenvalue analysis method to get the buckling modal,buckling eigenvalue and buckling load.Then,the post-bucking analysis was carried out by using arc-length method to get the buckling load,load path and failure load.Finally,the values obtained from above analysis were compared with the test results,which verified the correctness of the analysis methods.The buckling and post-buckling methods of stiffened composite panel were studied,and make a guideline to the carrying capability study of the stiffened composite panel.

关 键 词：复合材料 加筋壁板 仿真分析 试验验证 屈曲与后屈曲 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]