复杂载荷下复合材料螺栓连接预紧力松弛试验研究  

Experiment Research of Preload Loss in Composite Bolted Joint Under Complex Loads

作　　者：魏嘉兵 邹礼洋 杨浩然 贲强 袁大鹏 WEI Jiabing;ZOU Liyang;YANG Haoran;BEN Qiang;YUAN Dapeng(Wuhu State-Owned Factory of Machining,Wuhu 241000,China;Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]国营芜湖机械厂,芜湖241000 [2]南京航空航天大学,南京210016

出　　处：《航空制造技术》2024年第9期98-105,共8页Aeronautical Manufacturing Technology

摘　　要：本研究基于疲劳试验机,自主设计了复杂载荷螺栓松动试验装置。在不同的试验参数下开展了复杂载荷作用下螺栓连接结构松弛行为试验,系统地研究振动幅值、载荷类型对复杂载荷下螺栓连接结构松弛行为的影响。通过获取螺栓连接的实时残余夹紧力和螺栓螺母相对旋转角度,并结合光学显微镜分析复合材料板表面损伤形貌,进一步揭示复合材料螺栓连接松动机理。主要结论如下:当载荷幅值越大,螺栓连接残余夹紧力下降的值越大,连接结构越容易发生松弛行为;轴向幅值增大会导致复合材料板孔周位置损伤加重,横向幅值增大则会导致复合材料板板面磨损加重;复杂载荷的载荷类型对连接结构松弛行为会产生明显影响,与静拉伸载荷相比,振动载荷对螺栓连接残余夹紧力的影响更大。Based on the fatigue testing machine,this study independently designed bolt loosening test devices under complex loads.The loosening process of bolted joints under complex load had been investigated under many different experimental parameters,and the loosening behavior of bolted joints of different load amplitude and load type under complex load were systematically investigated.Combining the microscopic analysis using optical microscope and obtaining the real-time residual clamping force of bolt connection and the relative rotation angle of bolt and nut,this paper revealed loose mechanism of composite bolt connection.The main conclusions obtained in this study are as follows:When the load amplitude is larger,the residual clamping force of bolt connection decreases more,and the connection structure is more prone to relaxation.The increase of axial amplitude leads to the aggravation of the damage around the hole of the composite plate;The increase of transverse amplitude leads to the increase of wear of composite board surface;The load type of complex load obviously affects the relaxation behavior of the connection structure;Compared with static tension load,vibration load has greater influence on the residual clamping force of bolt connection.

关 键 词：复杂载荷 螺栓连接 螺栓松弛 复合材料 夹紧力 复合材料损伤 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程] V216.3