缝合复合材料T形连接件拉脱数值模拟  

Numerical Simulation of Stitched Composite T-Joints Under Pull-Out Load

作　　者：陈绍雄 朱书华[1] 周龙[1] 王星雨 CHEN Shaoxiong;ZHU Shuhua;ZHOU Long;WANG Xingyu(College of Aerospace Engineering,Nanjing University of Aeronautic&Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航空学院,南京210016

出　　处：《南京航空航天大学学报》2023年第1期44-50,共7页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家科技重大专项(Y2019-I-0018-0017)。

摘　　要：为研究缝线对缝合复合材料T形连接件拉脱承载能力的增强机理,建立了未缝合复合材料T形连接件的有限元模型,数值分析结果与已有实验数据吻合较好。同时根据缝合复合材料T形连接件在宽度方向上的平移对称性,通过在模型边界加入特定的边界条件建立了缝合T形连接件的简化模型来模拟结构的渐进损伤过程。在此基础上,进一步研究了缝线的位置和横截面积对T形连接件在拉脱载荷下力学性能的影响。结果表明:缝线位置越靠近三角区,缝线对结构最大承载能力的影响越大。当筋条和蒙皮缝合的位置处于三角区边缘时,较细的缝线会减弱结构的承载能力,而较粗的缝线则起大幅增强作用。In order to study the strengthening mechanism of stitching thread on the pull-out load-carrying capacity of stitched composite T-joints,a finite element model of unstitched composite T-joints is established.The numerical results are in good agreement with the existing experimental data.At the same time,according to the translational symmetry of stitched composite T-joints in the width direction,a simplified model of stitched T-joints is established by adding specific boundary conditions to the model boundary to simulate the progressive damage process of the structure.On this basis,the effects of the position and cross-sectional area of the stitching thread on the mechanical properties of T-joints under pull-out load are further studied.The results show that the closer the stitching thread is to the triangle area,the more influence of the stitching thread has on the maximum bearing capacity of the structure.When the stitching position of the stiffener and skin is at the edge of the triangle area,the stitching thread with the smaller cross-sectional area will weaken the bearing capacity of the structure,while the stitching thread with the larger cross-sectional area will greatly enhance it.

关 键 词：缝线 T形连接件 平移对称性 有限元方法 界面脱粘 

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] TB332[一般工业技术—材料科学与工程]