复合材料损伤结构胶接补强修补分析及设计  

THE ANALYSIS AND DESIGN OF THE ADHESIVE BONDING REPAIR OF THE DAMAGED COMPOSITE COMPONENTS

作　　者：孟凡颢[1] 陈绍杰[2] 董善艳[1] 童小燕[1] 

机构地区：[1]西北工业大学飞行器结构完整性研究所,西安710072 [2]沈阳飞机设计研究所,沈阳110035

出　　处：《飞机设计》2002年第1期18-21,共4页Aircraft Design

摘　　要：对复合材料层合板采用 2 0节点等参元、对于胶层采用节理单元建立有限元分析模型 ,并针对胶接补强修补的两种形式——贴补和挖补编制了相应的三维有限元分析程序 ,进行静力分析 ,获得了修补参数对修补效果的影响曲线 ,据此来初步确定最佳的修补参数。In this paper, the author set up a finite element analysis model, in which the author adopts the 20-node is oparametric brick element to plot the composite laminate and adopts the 16-node curved-surface joint element to plot the adhesive. Aiming at two types of bonded adhesive repair-scarf patch repair and extermal patch repair, the author designed a 3-dimension finite element analysis program, conducted static analysis and achieved the curves of the repair effect of the parameters, with which the optimal repair parameters can be primarily determined.

关 键 词：设计 复合材料 胶接修补 有限元分析 直升机 飞机结构 

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] V275.1