挖补修理平纹编织面板蜂窝夹芯结构侧向压缩渐进失效机理  

Progressive Failure Mechanism of Scarf Repaired in Honeycomb SandwichStructures with Plain Weave Panels under Edgewise Compression

作　　者：王轩[1] 马瑞云 周春苹 WANG Xuan;MA Ruiyun;ZHOU Chunping(College of Aeronautical Engineering,Civil Aviation University of China,Tianjin,300300;Aviation Key Lab of Science and Technology on High Performance Electromagnetic Windows,AVIC Research Institute for Special Structure of Aeronautical Composite,Jinan,250023)

机构地区：[1]中国民航大学航空工程学院,天津300300 [2]航空工业济南特种结构研究所高性能电磁窗航空科技重点实验室,济南250023

出　　处：《中国机械工程》2023年第6期727-738,共12页China Mechanical Engineering

基　　金：国家重点基础研究发展计划(20014CB046200);天津市科技计划(20YDTPJC00380);航空科学基金(2018ZF67011);中央高校基本科研业务费中国民航大学专项资金(3122019099)。

摘　　要：针对单侧面板挖补、单侧面板加芯子挖补、双侧面板加芯子挖补3种修理方式,采用一维阶梯挖补模型代替三维模型研究挖补修理平纹编织面板蜂窝夹芯结构侧向压缩渐进失效机理。建立能够模拟蜂窝壁损伤演化的有限元模型,利用内聚力模型模拟胶层损伤。试验和仿真结果表明,完好件和各种挖补方式试验件的破坏模式均为向非修补面板内凹的屈曲变形;各种挖补方式的侧压强度恢复率均在75%以上,大小排序为:单侧面板挖补、双侧面板加芯子挖补、单侧面板加芯子挖补;完好件和各种挖补方式试验件均未出现面板损伤,均出现蜂窝壁横向损伤和剪切损伤,且横向损伤均先出现,均在与发生大变形的蜂窝芯格相连的胶层处出现应力集中;蜂窝壁纵向损伤仅出现在单侧面板挖补件上,胶层损伤只出现在双侧面板加芯子挖补件上;芯子蜂窝壁损伤均发生在靠近替芯的母体芯材上。For three scarf repair methods of the unilateral panel repair,the unilateral panel and core repair,the bilateral panel and core repair,the one-dimensional stepped-scarf model was used instead of the three-dimensional model to study the progressive failure mechanism of scarf repaired in honeycomb sandwich structures with plain weave panels under edgewise compressive loads.A finite element model that might simulate the damage evolution of honeycomb wall was established.And the cohesive model was used to simulate the damages of the adhesive layers.The results show that the failure modes of pristine and repaired sandwich structures are the concave buckling deformations to the non-repaired panels.The recovery rate of edgewise compression strength of repaired sandwich structures is above 75%,and the data are ranked from largest to smallest as follows:the unilateral panel repair,the bilateral panel and core repair,the unilateral panel and core repair.No damages may be seen on the panels of pristine and repaired specimens.The transverse and shear damages occur on the honeycomb wall,and the former appears first.Stress concentration occurs at the adhesive layer connected to the honeycomb core with large deformation.The longitudinal damages of the honeycomb wall only appear on the unilateral panel repair specimens,and the damages of adhesive layer appear on the bilateral panel and core repair specimens.The damages of honeycomb wall occur on the parent core materials close to the replacement core.

关 键 词：复合材料 蜂窝夹芯结构 渐进失效分析 内聚力模型 挖补修理 

分 类 号：TB332[一般工业技术—材料科学与工程]