矫形力与垫片补偿对复合材料装配结构变形及螺栓夹紧力的影响  

Effect of Orthopedic Forces and Shim Compensation on Deformation of Composite Assembly Structure and Bolt Clamping Force

作　　者：赵付山 安鲁陵[1,2] 岳烜德 张永明 李雨霏 ZHAO Fushan;AN Luling;YUE Xuande;ZHANG Yongming;LI Yufei(College of Mechanical and Electronic Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Jiangsu Key Laboratory of Precision and Micro-manufacturing Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学机电学院,江苏南京210016 [2]南京航空航天大学江苏省精密与微细制造技术重点实验室,江苏南京210016

出　　处：《机械制造与自动化》2024年第4期42-47,共6页Machine Building & Automation

基　　金：国家自然科学基金项目(5197051852);江苏省精密与微细制造技术重点实验室基本科研业务重点项目(ZAA1400105)。

摘　　要：飞机复合材料构件成型精度较低进而导致装配间隙,可施加矫形力减小甚至消除间隙,若存在较大间隙需施加垫片进行补偿。以复合材料壁板为对象,通过试验的方法,观测壁板在矫形、螺栓连接以及撤矫形力过程的变形,以及矫形力撤出后螺栓夹紧力的变化。结果表明:壁板变形量随矫形力的增大而增大,相应垫片补偿尺寸减小,当矫形力达一定程度时,变形量趋于稳定;撤矫形力后,壁板回弹量随矫形力值近似呈线性关系,当矫形力达150 N时,最大回弹量为0.117 mm,占装配间隙的7.83%;撤矫形力后各区域螺栓夹紧力都有增加趋势,其中壁板与骨架存在间隙的区域,夹紧力增长相对明显,夹紧力变化最大为50 N,增长率为1%左右。The assembly clearance caused by low accuracy of aircraft composite component formation can be reduced or even eliminated by applying a straightening force,and a larger gap can be compensated by applying a shim.Composite wall plate was taken as reserch subject to observe its deformation during the process of straightening,bolting and withdrawal of straightening force as well as the change of bolt clamping force after the withdrawal of straightening force by the test method.The results show that the deformation of the wall plate increases with the increase of the orthopedic force,the corresponding shim compensation size decreases,and when orthopedic forces reach a certain degree,the deformation tends to stabilize.After the withdrawal of the orthopedic force,the rebound of the wall plate assumes approximate linear relationship with the value of the orthopedic force,and when orthopedic forces reach 150 N,the maximum rebound is 0.117 mm,accounting for 7.83%of the assembly gap.After the withdrawal of the orthopedic force,the bolt clamping force in each area has a tendency to increase,among which,the region where the gap between the wall plate and the skeleton exists,the clamping force grows relatively obviously,and when the maximum change in clamping force is 50 N,the growth rate reaches around 1%.

关 键 词：飞机装配 复合材料 矫形力 填隙补偿 

分 类 号：V262.4[航空宇航科学与技术—航空宇航制造工程]