Experimental and numerical studies on buckling and post-buckling behavior of T-stiffened variable stiffness panels  

作　　者：Yan HUANG Yahui ZHANG Bin KONG Jiefei GU Zhe WANG Puhui CHEN 

机构地区：[1]State Key Laboratory of Mechanics and Control of Mechanical Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China [2]AVIC Aviation Power Control System Research Institute,Wuxi 214063,China [3]Chengdu Aircraft Design and Research Institute,Aviation Industry Corporation of China,Chengdu 610091,China [4]School of Mechanical Engineering,Jiangnan University,Wuxi 214122,China [5]School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China [6]China National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi’an 710065,China

出　　处：《Chinese Journal of Aeronautics》2024年第10期459-470,共12页中国航空学报（英文版）

基　　金：Supported by the National Natural Science Foundation of China(No.11902124).

摘　　要：Currently,experimental research on variable stiffness design mainly focuses on laminates.To ensure adaptability in practical application,it is imperative to conduct a systematic study on stiffened variable stiffness structures,including design,manufacture,experiment,and simulation.Based on the minimum curvature radius and process schemes,two types of T-stiffened panels were designed and manufactured.Uniaxial compression tests have been carried out and the results indicate that the buckling load of variable stiffness specimens is increased by 26.0%,while the failure load is decreased by 19.6%.The influence mechanism of variable stiffness design on the buckling and failure behavior of T-stiffened panels was explicated by numerical analysis.The primary reason for the reduced strength is the significantly increased load bearing ratio of stiffeners.As experimental investigations of stiffened variable stiffness structures are very rare,this study can be considered a reference for future work.

关 键 词：Variable stiffness composite BUCKLING POST-BUCKLING Finite element method Stiffened panels 

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]