加筋壁板大开口结构稳定性分析及试验验证  

Stability Analysis and Test Verification of Stiffened Panel with Large Cutout

作　　者：余明[1] 凌晓涛 史劲松[1] 

机构地区：[1]中航工业第一飞机设计研究院,陕西西安710089

出　　处：《航空科学技术》2015年第3期62-66,共5页Aeronautical Science & Technology

摘　　要：为了研究加筋壁板大开口结构的压缩承载极限问题,规划了两组具有不同设计参数的试验件进行了静力试验,并同时采用了线性特征值法以及非线性的弧长法对其压缩极限进行了对比分析。在采用弧长法分析时,引入了模态扰动技术,而且考虑了材料的弹塑性性质。计算结果与试验的对比表明:针对复杂结构稳定性问题,屈曲特征值法具有较大局限性,而结合模态扰动的弧长法对这种复杂的加筋壁板类结构压缩极限的分析精度较好。通过分析给出了加筋壁板大开口结构设计的一些建议。To study the problem of the ultimate compression strength of the stiffened panel with large cutout, introduced the test of two group units with different structure parameters, and analyzed their ultimate compression strength by both the liner eigenvalue method and the nonlinear arc-length method. During the nonlinear arc-length analyzing, the modal perturbation technique was introduced, and the material elastic-plastic properties was also considered. The comparison between the experimental and numerical results shows that eigenvalue method to calculate the critical load of complex structure is not applicable, and a ful y nonlinear method, such as the modiifed arc-length method, should be used instead. Final y, advice on designing such a stiffened panel with large cutout were provided.

关 键 词：加筋壁板 大开口结构 弧长法 稳定性 后屈曲 

分 类 号：V214.42[航空宇航科学与技术—航空宇航推进理论与工程] V216.13