摘要
抽芯铆钉广泛应用于航空制造与装配领域,其芯杆断面相对钉套头表面凸出量(芯杆齐平度)有定量规定标准,但芯杆齐平度对于连接结构力学性能的影响并不明确。针对这一问题,开展了不同芯杆齐平度下装配结构的静力学性能及疲劳性能试验,并对结构的装配以及静力学性能进行了仿真验证。通过试验探究发现,芯杆齐平度合格样件剪切力破坏强度平均值为9570.535 N,标准差为107.001 N,芯杆齐平度不合格样件剪切力破坏强度平均值为9532.14 N,标准差为327.261 N,两者标准差差异显著,可见相较于超差试样,合格试样结构稳定性更强;疲劳试验中芯杆齐平度合格样件疲劳循环次数平均值为456770次,芯杆齐平度不合格样件疲劳循环次数平均值为456022.7次,疲劳强度受该方面的影响较小。对抽铆的仿真发现,两种情况下芯杆的绝对干涉量几乎没有区别,该结论解释了为何两组试验的剪切力没有太大区别,并且在仿真过程中发现两者的力–位移曲线几乎没有区别,进一步验证了试验结论。
The pulling core rivet is widely used in the field of aviation manufacturing and assembly.There is a quantitative standard for the protrusion of the core rod section relative to the surface of the nail sleeve head(flatness of core rod),but the influence of flatness of core rod on the mechanical properties of the connected structure is not clear.In order to solve this problem,the static and fatigue performance tests of the assembly structure induced by the flatness of the core rod were carried out.The assembly and static performance of the structure are simulated and verified.Through experimental research,it is found that the average shear failure strength of samples with qualified core rod flatness is 9570.535 N,and the standard deviation is 107.001 N;the average shear failure strength of samples with unqualified core rod flatness is 9532.14 N,and the standard deviation is 327.261 N.Compared with out-of-tolerance samples,the standard deviation of qualified samples is more stable.In the fatigue test,the average number of fatigue cycles of qualified core rod evenness samples is 456770,and the average number of fatigue cycles of unqualified core rod evenness samples is 456022.7,so the fatigue strength is less affected by this aspect.The simulation of riveting shows that there is almost no difference in the absolute interference of the core rod under the two conditions.This conclusion explains why there is not much difference in the shear force between the two groups of tests,and it is found that there is almost no difference in the force-displacement curves between the two groups during the simulation process,which further verifies the test conclusion.
作者
林伟
邱建平
史建猛
周莹
郝浩杰
张斌
LIN Wei;QIU Jianping;SHI Jianmeng;ZHOU Ying;HAO Haojie;ZHANG Bin(AVIC Xi’an Aircraft Industry Group Company Ltd.,Xi’an 710089,China)
出处
《航空制造技术》
CSCD
北大核心
2024年第9期20-27,共8页
Aeronautical Manufacturing Technology
关键词
抽芯铆钉
芯杆齐平度
静力学性能
疲劳性能
数值模拟
Core-pulling rivet
Core rod flatness
Static performance
Fatigue performance
Numerical simulation
