干涉配合对飞机机翼螺栓连接结构力学性能的影响

为了研究干涉量对螺栓连接结构力学性能的影响,以航空工程中常用的飞机机翼螺栓干涉连接结构模型为研究对象,采用了基于试验验证的有限元分析方法,通过试验验证了所建立的螺栓连接结构三维弹塑性有限元分析模型的可靠性,在此基础上建立了6种不同干涉量下飞机机翼螺栓连接结构的参数分析模型,系统地分析不同干涉量对螺栓连接结构孔边应力分布、初始刚度以及承载能力的影响并进行对比分析,结果如下:对飞机机翼螺栓连接结构采取合适的干涉配合可以明显改善孔边结构的应力分布,减小应力集中情况;在所选取的干涉量范围内(0～2.5％),随着干涉量的增大,孔边结构的峰值应力距离孔边越远;当干涉量为1.5％ 时,孔边的峰值应力最小,同时当干涉量为1.5％ 时,结构的初始刚度和承载能力提高程度均为最大,分别提高了14.1％ 和9.33％.

Effect of Interference Fit on Mechanical Properties of Aircraft Wing Bolt Connection Structure

In order to study the influence of the interference on the mechanical performance of the bolt connection structure, research work is made by adopting the finite element analysis method based on the experimental verification taking the model of bolt interference connection structure of aircraft wing commonly used in the aviation engineering as an object of study. Firstly, the built model is verified by the test based on the reliability of the three dimensional elastic plastic finite element analysis model of bolted connection structure. Secondly, a parameter analysis model of bolt connection structure of aircraft wing under six different interference quantities is established. The influence of different interference quantities on the stress distribution, initial stiffness and bearing capacity of bolt connection structure is systematically analyzed and compared. Finally, the results show that the stress distribution and the stress concentration of the bolt connection structure can be improved obviously by using the appropriate interference fit. In the selected interference range (0~2.5%), with the increase of the interference amount, the peak stress of the hole edge structure is farther away from the hole edge. When the interference amount is 1.5%, the peak stress of the hole edge is the smallest. At the same time, when the interference amount is 1.5%, the initial stiffness and bearing capacity increase by 14.1% and 9.33% respectively.