摘要
详细分析了旋翼调整片粘接剥离破坏过程和应力分布变化,并研究了粘接宽度和胶层厚度对粘接强度的影响。使用共固化制备相应的粘接试样,通过剥离试验得到接头的破坏模式及载荷-位移曲线。研究结果表明:接头有限元数值分析结果与试验相契合,接头破坏形式为调整片粘接界面的破坏,破坏为从左向右和由边向中逐渐发生失效;粘接强度随胶接宽度的增加而提高,但增长速度逐步变缓,80 mm为较优搭接宽度值;粘接强度受胶层厚度影响较小,增加厚度时粘接强度先缓慢增加后下降。
The failure process and stress distribution change of rotor blade tab were analyzed in details,andthe influence of bonding width and thickness of adhesive layer on bonding strength were studied.The correspondingbonding sample was prepared by co-curing process,the failure mode and load-displacement curve of the joint wereobtained by peel test.The research results showed that finite element numerical analysis result was consistent withthe test.The failure mode of the joint was the bonding interface failure of motor blade tab,and the failure wasgradually from left to right and from side to center.The bonding strength increased with the increase of bondingwidth,but the growth rate gradually slowed down,the optimum bonding width was 80 mm.The bonding strength wasless affected by the thickness of adhesive layer,and the bonding strength increased slowly first and then decreasedwith the increase of thickness.
作者
程凯
李德宝
祖磊
张骞
宫诚
Cheng Kai;Li Debao;Zu Lei;Zhang Qian;Gong Cheng(School of Mechanical Engineering,Hefei University of Technology,Hefei 230000,Anhui,China;Hefei United Aircraft Technology Co.,Ltd.,Hefei 238000,Anhui,China)
出处
《中国胶粘剂》
CAS
北大核心
2020年第4期40-44,52,共6页
China Adhesives
关键词
复合材料
胶接搭接
应力分布
破坏模式
数值分析
composite material
bonded lap joint
stress distribution
failure mode
numerical analysis
