南京航空航天大学学报2025，Vol.57Issue(1)：109-119,11.DOI:10.16356/j.1005-2615.2025.01.011
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
陈然 1张迪 1蔡登安1
作者信息
- 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
- 折叠
摘要
Abstract
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Key words
hybrid composites/low-velocity impact/compression after impact/failure mode/residual compression strength引用本文复制引用
陈然,张迪,蔡登安..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[J].南京航空航天大学学报,2025,57(1):109-119,11.
