碳/芳纶混杂复合材料蜂窝夹芯板低速冲击及冲击后压缩实验研究  

Experimental Study on Low⁃Velocity Impact and Compression After Impact of Carbon/Aramid Hybrid Composite Honeycomb Sandwich Panels

作　　者：陈然[1] 张迪[1] 蔡登安[1] CHEN Ran;ZHANG Di;CAI Deng’an(State Key Laboratory of Mechanics and Control for Aerospace Structures,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航空航天结构力学及控制全国重点实验室,南京210016

出　　处：《南京航空航天大学学报(自然科学版)》2025年第1期109-119,共11页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：通过低速冲击和冲击后压缩试验,探讨了不同复合材料面板和Nomex蜂窝组成的夹芯板在不同能量冲击损伤后的压缩承载行为、失效模式及失效机理。通过无损检测C扫描、Micro-CT和DIC数字测量技术,获得试样的失效模式。试验结果表明,材料损伤模式主要包括面板纤维断裂、基体和纤维界面脱粘、基体开裂、芯材剪切破坏以及芯材压溃。碳/芳纶混杂复合材料夹层结构相较于碳纤维复合材料夹层结构具有更好的层间性能,且层间混杂结构相较于层内混杂结构具有更高的压缩刚度和剩余压缩强度。The compressive bearing behavior,failure mode and failure mechanism of sandwich panels composed of different composite panels and Nomex honeycomb are discussed through low-velocity impact and compression after impact tests.The failure modes of the specimen are obtained by non-destructive C-scan tests,Micro-CT and DIC digital measurements.The results show that the material damage modes mainly include panel fiber fracture,matrix and fiber interface debonding,matrix cracking,shear failure and crushing of core material.Compared with the carbon fiber composite sandwich structure,the carbon/aramid hybrid composite sandwich structure has better interlaminar properties.Furthermore,the interlayer hybrid structure has higher compressive stiffness and residual compressive strength than the intralayer one.

关 键 词：混杂复合材料 低速冲击 冲击后压缩 失效模式 剩余压缩强度 

分 类 号：TB332[一般工业技术—材料科学与工程]