高锁螺栓装配的最佳干涉量实验与仿真研究  

EXPERIMENT AND SIMULATION RESEARCH OF THE OPTIMUM INTERFERENCE OF HI-LOCK ASSEMBLY

作　　者：谢阶栋 陈果[1] 曾馨靓 舒茂盛 罗云 高红 郑其辉 XIE JieDong;CHEN Guo;ZENG XinLiang;SHU MaoSheng;LUO Yun;GAO Hong;ZHENG QiHui(College of Civil Aviation,Nanjing University of Aeronautics and Astronautics,Nanjing 211016,China;Chengdu Aircraft Industrial (Group)Co.,Ltd.,Chengdu610092,China;Chengdu Aircraft Design &Research Institute ,Chengdu610041,China)

机构地区：[1]南京航空航天大学民航学院,南京211016 [2]成都飞机工业(集团)有限责任公司,成都610092 [3]成都飞机设计研究所,成都610041

出　　处：《机械强度》2018年第6期1321-1329,共9页Journal of Mechanical Strength

基　　金：国家自然科学基金项目(51175419);成都飞机工业(集团)有限责任公司项目资助~~

摘　　要：目前我国飞机高锁螺栓装配标准均是沿用国外标准,缺乏相关理论和试验研究。针对某型飞机铝合金结构,通过疲劳试验和有限元仿真相结合的方法,研究了高锁螺栓干涉量在不同夹层厚度的基体上对结构件的疲劳增益机理。首先,设计并进行疲劳试验,对疲劳试验结果进行S-N曲线分析、细节疲劳额定值(DFR)分析及断裂位置分析。然后,利用有限元法对试验件建模仿真,对试验现象进行解释,对干涉配合疲劳增益机理进行研究。最后,综合细节疲劳额定值结果与有限元仿真结果得到高锁螺栓装配的标准建议值,对现有安装规范进行验证,从而保障某型飞机的装配质量。At present ,the high lock bolt assembly standard of our country are come from abroad ,lack of relevant theoretical and experimental research.Fatigue gain mechanism of high lock bolt interference on the base of different layer thickness is researched ,through the method of combining the fatigue test and finite element simulation in a certain type of aircraft aluminum alloy structure.First,the fatigue test was designed and tested,and the results were analyzed by S-N curve,detail fatigue rating(DFR)and fracture location.Then,the finite element modeling and simulation are used to explain the experimental phenomena,and the mechanism of the interference fit to the fatigue gain is studied.Finally,the comprehensive detail fatigue rating results and the finite element simulation results are obtained,which are the standard recommended values of the high lock bolt assembly,and verified existing installation specifications,ensure the assembly quality of a certain type of aircraft.

关 键 词：干涉配合 高锁螺栓 疲劳强度 有限元法 细节疲劳额定值 

分 类 号：V262.4[航空宇航科学与技术—航空宇航制造工程]