复合材料加筋壁板的蒙皮屈曲研究  

作　　者：唐维 朱小龙 王乐 

机构地区：[1]中航成飞民用飞机有限责任公司,成都610091

出　　处：《科技创新与应用》2023年第14期65-69,共5页Technology Innovation and Application

摘　　要：该文给出一种能够准确施加纯轴压和纯剪切载荷的壁板屈曲试验加载方案,并通过有限元仿真分析对试验方案进行验证。在此基础上,采用数值试验、理论计算和工程分析3种方法研究某型无人机机翼帽型长桁壁板的蒙皮轴压和剪切屈曲临界载荷,根据数值试验结果,完善工程分析中的蒙皮尺寸截取和边界条件确定方法。结果表明,蒙皮屈曲工程分析时,帽型长桁为蒙皮约束,金属肋为简支约束,蒙皮宽度取长桁凸缘外侧间距,可以准确计算帽型长桁壁板的蒙皮屈曲临界载荷,与数值试验误差最大为6.36%。In this paper,a panel buckling test loading scheme capable of accurately applying pure axial compression and pure shear load is presented,and the test scheme is validated by finite element simulation analysis.The skin's axial compression and the critical load for shear buckling at the cap-stringer stiffened panel of a certain unmanned aerial vehicle wing are studied by three methods including numerical test,theoretical calculation and engineering analysis.Based on the result of numerical test,the methods for capturing skin dimensions and identifying boundary conditions in engineering analysis are improved.The results show that in the analysis of skin buckling engineering,the cap long truss is skin constraint,the metal rib is simply supported constraint,and the skin width is the outer distance of long truss flange,which can accurately calculate the skin buckling critical load of cap long truss wall plate.The maximum error between the skin buckling load and the numerical test is 6.36%.

关 键 词：复合材料蒙皮 帽型长桁壁板 稳定性试验 轴压屈曲 剪切屈曲 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]