基于子模型法的复合材料机翼蒙皮稳定性分析  

Stability Analysis of Composite Wing Skin Based on Sub-model Method

作　　者：孙喜桂 聂小华[1] 常亮[1] SUN Xigui;NIE Xiaohua;CHANG Liang(Aircraft Strength Research Institute of China,Xi’an 710065)

机构地区：[1]中国飞机强度研究所,西安710065

出　　处：《纤维复合材料》2023年第2期15-18,共4页Fiber Composites

基　　金：民用飞机专项科研(MJZ3-2N21)。

摘　　要：某型无人机机翼采用蜂窝夹层结构,本文利用有限元方法对其进行稳定性分析。为降低计算量和局部屈曲模态的影响,在整体模型中提取主翼盒作为子模型,并在主翼盒边界上施加从整体模型中提取的位移约束,得到了机翼蒙皮的临界屈曲载荷因子,与全机静力试验结果对比,试验时该处发生屈曲,分析得到的临界屈曲载荷与试验得到的临界屈曲载荷误差为6%。有限元分析结果表明,加厚蜂窝夹层厚度可以提高机翼蒙皮的屈曲载荷因子。本文可为机翼蒙皮的稳定性分析提供方法。The wing of a certain type of UAV is made of honeycomb sandwich structure.The stability of the wing is analyzed by finite element method in this paper.In order to reduce the computation and the influence of local buckling modes,the main wing box is extracted from the global model as a sub-model,and the displacement constraints are applied to the boundary of the sub-model,finally the critical buckling load factor of the wing skin is obtained.Compared with static test results of the whole UAV,buckling occurs at the same position during the test,and the error between the critical buckling load obtained by analysis and the critical buckling load obtained by the test is 6%.The results of finite element analysis show that the thickening of honeycomb sandwich can improve the buckling load factor of wing skin.This paper provides a method for the stability analysis of wing skin.

关 键 词：蜂窝夹层 子模型法 稳定性分析 屈曲载荷因子 

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]