复合材料蜂窝夹层结构轴压载荷下总体屈曲计算研究  

General stability study of composite honeycomb structure under compression load

作　　者：杜正兴[1] 刘洪权[1] 

机构地区：[1]中航工业第一飞机设计研究院,西安710089

出　　处：《强度与环境》2015年第6期11-16,共6页Structure & Environment Engineering

摘　　要：对两种芯层厚度的复合材料蜂窝夹层板进行轴压载荷下的稳定性试验,给出了试验件的屈曲载荷及破坏形式。分别采用四种工程方法及线性与非线性有限元方法对轴压载荷下蜂窝夹层板的屈曲破坏载荷进行计算,根据试验结果,对各类方法的计算结果进行了误差分析并给出了其使用建议。对文献[8]中的方法,因计算过程简单,易于程序化实现,推荐在型号设计中使用。General stability test of composite honeycomb panels with two different thickness of the Honeycomb Core under compression load was carried out in this paper. The buckling loads and the damage modes of the specimens were also obtained. The general buckling loads of the honeycomb panels under compression load were calculated using four different engineering methods and both linear and nonlinear finite element methods. The suggestions of each method were given after analysis and comparison of the calculated results and the test results. Engineering method in reference[8] which is easy to program and simple to calculate was recommended to use in the aircraft design phase.

关 键 词：蜂窝夹层结构 总体稳定性 轴压载荷 有限元 屈曲计算 

分 类 号：V416.2[航空宇航科学与技术—航空宇航推进理论与工程]