蒙皮局部屈曲对加筋圆柱壳轴压承载力的影响  

Influence of skin pocket buckling on the axial loading capacity of stiffened cylindrical shells

作　　者：张守宇 王会平 曹景乐 贺丹[1,3] ZHANG Shouyu;WANG Huiping;CAO Jingle;HE Dan(Key Laboratory of Liaoning Province for Composite Structural Analysis of Aerocraft and Simulation,Shenyang Aerospace University,110136 Shenyang,China;Beijing Institute of Astronautical Systems Engineering,100076 Beijing,China;Hunan Inno China Advanced Material Co.,Ltd.,414000 Yueyang,China)

机构地区：[1]沈阳航空航天大学辽宁省飞行器复合材料结构分析与仿真重点实验室,沈阳110136 [2]北京宇航系统工程研究所,北京100076 [3]湖南中创空天新材料股份有限公司,岳阳414000

出　　处：《应用力学学报》2025年第2期298-305,共8页Chinese Journal of Applied Mechanics

基　　金：国家重点研发计划资助项目(No.2020YFA0711104)。

摘　　要：早期的网格加筋圆柱壳结构设计指南,如NASA SP-8007,建议通过采用足够的纵筋数目和蒙皮厚度来避免结构发生蒙皮局部屈曲。但这一设计要求缺乏有力的支撑证据,且有可能会提高工艺成本和结构重量。为了厘清蒙皮局部屈曲对结构产品轴压承载能力的影响,分别基于线性解析法、非线性有限元法以及单点扰动载荷法对某典型网格加筋圆柱壳及其等刚度改型结构进行了详细的计算和对比分析。结果表明,对于无缺陷的完美结构,蒙皮局部屈曲会显著降低其结构承载力,而对含有初始缺陷的实际结构,蒙皮局部屈曲对其结构承载力并无影响。因此在结构设计时,不需要刻意地规避蒙皮局部屈曲。Early guidelines for grid-stiffened cylindrical shells design,such as SP-8007 of NASA,suggest that the sufficient number of stringers and thickness of skin should be employed to avoid skin pocket buckling.This principle is lack of solid evidence and may lead to redundant weight and unnecessary cost.To clarify the influence of skin pocket buckling on the axial load bearing capacity of stiffened cylinders,a typical subscale cylinder and its modified versions are analyzed and compared in detail on the basis of linear buckling theory,nonlinear finite element method,and single perturbation load approach,respectively.The results indicate that although the skin pocket buckling can significantly reduce the buckling load of an idealized perfect structure,it has little influence on a real one with inevitable imperfection.Therefore,it is unnecessary to avoid skin pocket buckling in the primary design phase.

关 键 词：加筋圆柱壳 蒙皮局部屈曲 非线性屈曲 有限元分析 单点扰动载荷法 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程]