某型飞机零号框损伤修复技术研究  

Research on No. 0 Frame Injury Repair Technology

作　　者：谢大叶 邹仕军[2] 王石[3] 

机构地区：[1]中航工业沈阳飞机工业(集团)有限公司 [2]中国人民解放军驻沈阳飞机工业(集团)有限公司军事代表室 [3]中国人民解放军九三七零五七部队

出　　处：《航空制造技术》2015年第5期64-67,共4页Aeronautical Manufacturing Technology

摘　　要：针对某型飞机中机身零号框多处损伤的现象,根据损伤产生特点及结构描述,利用有限元方法,模拟零号框局部修补后状态,对修复该腹板的可行性进行分析,并对其进行加载计算,结果表明:修补后零号框无法满足强度要求;在更换零号框腹板过程中,采用组合式引孔衬套替代原引孔方式,解决了二次引孔易超差的难题,为今后族类飞机框腹板及改型机的修复提供了参考。In view of multiple site damage phenomenon the fuselage No.0 frame of a certain type of aircraft, according to the description of the structure and characteristics of damage, using the fi nite element method to simulate No.0 frame local state after repair, the feasibility of repairing the web is analyzed and the results show that the load calculation repair cannot meet the strength requirements. In the replacement of the No.0 frame web process, the combined guide hole bushing is adopted to replace the original pilot hole method, which solves the problem of poor hole two times cited prone, provides reference value for repair and modifi cation in the future generation aircraft.

关 键 词：零号框 损伤 有限元 修复方案 引孔衬套 

分 类 号：V267[航空宇航科学与技术—航空宇航制造工程]