某型飞机复合材料壁板穿孔的结构修理研究  

On Structural Repair of Composite Panel Perforation of a Certain Type of Aircraft

作　　者：王博 赵东平 李锋 李荣 王飞 褚昱博 WANG Bo;ZHAO Dong-ping;LI Feng;LI Rong;WANG Fei;CHU Yu-bo(School of Aircraft Engineering,Xi'an Aeronautical University,Xi'an 710077,China)

机构地区：[1]西安航空学院飞行器学院,西安710077

出　　处：《西安航空学院学报》2020年第5期13-17,79,共6页Journal of Xi’an Aeronautical Institute

基　　金：陕西省自然科学基础研究计划项目(2019JM-435);西安航空学院校级科研基金(2019KY1228)。

摘　　要：针对某型飞机复合材料壁板出现穿孔损伤的问题,为恢复该类壁板的强度,采用螺接外补强板法,计算出补强板和垫板的尺寸、螺栓的数目以及螺栓的排布形式,建立壁板穿孔修理的三维模型。利用有限元软件模拟分析飞机飞行时壁板的受力情况,得到修复后壁板的位移、应变以及螺栓所受应力的情况。研究表明,采用螺接外补强板法对复合材料壁板穿孔进行修理,可以很好的恢复壁板穿孔处的强度,可为同类飞机构件的修理提供工程参考。Aiming at the problem of perforation damage in composite panel of a certain type of aircraft,and to restore the strength of this kind of panel,the sizes of reinforcing plate and backing plate,and the number and arrangement of bolts are calculated by using the method of bolted external reinforcing plate so as to establish the three-dimensional model for repairing the perforation of panel.The finite element software is employed to simulate and analyze the stress of the panel in flight,and the displacement,strain and bolt stress of the repaired panel are obtained.The results show that the strength of the perforated composite panel can be restored by using the method of bolted external reinforcement plate,which can provide engineering reference for the repair of similar aircraft components.

关 键 词：飞机结构修理 复合材料壁板 钛合金 螺栓 有限元分析 

分 类 号：V267.4[航空宇航科学与技术—航空宇航制造工程]