复合材料蜂窝夹芯修补结构弯曲特性与温度相关性研究  

STUDY ON THE RELATIONSHIP BETWEEN BENDING CHARACTERISTICS AND TEMPERATURE OF COMPOSITE HONEYCOMB SANDWICH REPAIR STRUCTURE

作　　者：余芬[1] 郭拓 何振鹏 但敏[1] YU Fen;GUO Tuo;HE Zhen-peng;DAN Min(Aeronautical Engineering 1nstitute,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300

出　　处：《复合材料科学与工程》2021年第4期41-49,共9页Composites Science and Engineering

基　　金：天津市自然科学基金项目(18JCQNJC05400);天津市教委自然科学项目(2018KJ240);中国民航大学实验技术创新基金(2018CXJJ19)。

摘　　要：建立复合材料蜂窝夹芯修补结构的渐进损伤分析模型,研究修补后蜂窝夹芯结构在弯曲载荷作用下的极限承载能力及损伤破坏模式,并进一步研究修补结构弯曲性能与温度的相关性。通过编写VUMAT子程序,设置补片以及蜂窝损伤板的失效准则及刚度退化模式,选用Cohesive单元以模拟修补结构中胶层的损伤状况,完成复合材料蜂窝夹芯修补结构的渐进损伤分析。研究结果表明:结构弯曲承载能力和胶层的粘结能力受温度影响较大,结构弯曲承载强度随温度的升高而减小,且脱粘失效会破坏结构的完整性;蜂窝夹芯结构面板基体损伤首先发生在90°方向铺层处,纤维基体剪切损伤首先发生在面板0°铺层处,并沿垂直于施载方向扩展至自由边界。The progressive damage analysis model of composite honeycomb sandwich repair structure is established,and the ultimate bearing capacity and damage failure mode of repaired honeycomb sandwich structure under bending load are studied,and the correlation between bending performance and temperature of repaired structure is further studied.By programming the VUMAT subroutine,setting the failure criteria and stiffness degradation mode of the patch and honeycomb damaged plate,and using the cohesive element to simulate the repair adhesive layer,the progressive damage analysis of composite honeycomb sandwich repair structure was completed.The results show that the bending bearing capacity of the structure and the bonding capacity of the adhesive layer are greatly affected by the temperature,the bending strength of the structure decreases with the increase of the temperature,and the debonding failure will damage the structural integrity.The matrix damage of the honeycomb sandwich panel first occurs at the 90°ply,and the fiber matrix shear damage first occurs at the 0°ply,and extends to the free boundary.

关 键 词：复合材料蜂窝夹芯结构 胶接修补 渐进损伤模型 VUMAT子程序 温度相关性 

分 类 号：TB332[一般工业技术—材料科学与工程]