缝合复合材料T型加强板强度仿真研究  

Simulation Study on Strength of Stitched Composite T-Stiffener Panels

作　　者：何周理 黄龙辉 HE Zhouli;HUANG Longhui(COMAC Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)

机构地区：[1]中国商飞上海飞机设计研究院,上海201210

出　　处：《航空制造技术》2024年第4期118-122,131,共6页Aeronautical Manufacturing Technology

摘　　要：为提高复合材料筋条与蒙皮的连接界面强度,局部缝合技术是一种有效的方法。分别对无损伤缝合加筋板和含冲击损伤缝合加筋板采用内聚力模型模拟界面层、粘接元模拟缝合进行有限元建模(FEM)计算分析,并与轴压试验结果进行对比。两组试验结果与有限元计算分析结果偏差均不大于8.5%,表明采用有限元模拟界面层和缝线的方法是可行的;试验结果和有限元计算结果显示,当蒙皮与筋条尚未发生剥离的情况下,缝合对复合材料加筋板的压缩承载能力影响不显著。In order to improve the interface strength between composite ribs and skin,stitching is an effective method.Finite element model(FEM)analysis and axial compression test were carried out on the non damage stitched stiffened panel and the impact damage stitched stiffened panel.The cohesive zone model was used to simulate the interface and the bonding element was used to simulate the stitching for FEM analysis.The deviation between the test results and FEM results is no more than 8.5%,which shows that the FEM of cohesive model and bonding element is feasible.The test results and the FEM results both show that the stitching has no significant effect on the compressive capacity of composite stiffened panel.

关 键 词：复合材料 缝合 冲击损伤 压缩强度 有限元模拟 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]