飞机某典型螺栓连接件的振动疲劳试验研究  

Study on Vibration Fatigue Testing of Aircraft Typical Bolt Connector

作　　者：李益萱[1] 王龙[1] Li Yixuan;Wang Long(Aircraft Strength Research Institute, Xi'an 710065, China)

机构地区：[1]中国飞机强度研究所

出　　处：《机械科学与技术》2019年第9期1401-1405,共5页Mechanical Science and Technology for Aerospace Engineering

摘　　要：为确定不同螺栓连接形式与不同名义厚度的某典型结构连接件的振动疲劳极限寿命,并比较其振动疲劳性能,本文针对连接件要求考核部位的特殊性,提出了简支结构的夹具设计方法,在经过有限元模拟计算及在模态试验中进行了验证考核后,成功应用于正式试验中,另外,试验采用小量级振动条件下应变数值曲线拟合得到大量级振动条件下应变值,完成了试验应变-寿命曲线的绘制。通过此次试验研究表明:1)简支结构的夹具设计被证明适用于此类搭接结构的螺栓连接件,可以应用在此后类似的振动试验中;2)复材名义厚度为5 mm的单排双钉连接件,在同样的应变水平下,具有最长的振动疲劳寿命,即振动疲劳性能最好;3) 4种不同形式的螺栓连接件,振动疲劳破坏位置均为金属部分,在下一步的设计中需更换金属材料,加强金属搭接板的动强度。In order to determine the vibration fatigue limit of the typical bolt connectors with different connection types and different nominal thicknesses, and compare the vibration fatigue characteristics of them, the vibration fatigue tests were carried out. According to the special requirements of the testing, a simply-supported fixture was designed, which was then verified and optimized by the finite element software and modal testing. This simply-supported fixture was proved meeting the design requirements. Furthermore, the strain values of the large-magnitude vibration were obtained by the curve-fitting method from the strain values of the small-magnitude vibration. By making the curve fitting, the strain-life curves of the four type connections were depicted. At last, the testing was completed successfully, and it can be concluded that: 1) the simply-supported fixture dose apply to the vibration testing of the bolt connections and can be used in the same kind testing later;2) in the situation of the same strain level, the double-row-screw bolt connection has the longest vibration fatigue life, that is to say it has the best vibration fatigue characteristic;3) the failure part of all connections is the metal part, so in the next step of designing, the metal type should be substituted and the dynamic strength of it should be reinforced.

关 键 词：振动疲劳 简支夹具设计 应变拟合 疲劳极限 振动试验 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]