直升机变距拉杆杆端自润滑关节轴承的力学分析和损伤特性  

Mechanical analysis and damage characteristics of self-lubricating joint bearings of helicopter variable-pitch tie rod ends

作　　者：周长春[1] 杨永生 谭德强 杨晓强[1] 贺强[1] 胡月 ZHOU Changchun;YANG Yongsheng;TAN Deqiang;YANG Xiaoqiang;HE Qiang;HU Yue(Aviation Engineering College,Civil Aviation Flight University of China,Guanghan Sichuan 618307,China)

机构地区：[1]中国民用航空飞行学院航空工程学院,四川广汉618307

出　　处：《航空动力学报》2022年第5期924-933,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(52105132);四川省应用基础研究项目(2020YJ0192、2021YJ0537);四川省科技成果转移转化平台项目(2019ZHCG0139);中国民用航空飞行学院面上项目(J2021-044)。

摘　　要：以R44直升机主旋翼变距拉杆杆端自润滑关节轴承为研究对象,用三维建模软件Solidworks建立其旋转摆动的有限元模型并导入到有限元分析软件Ansys Workbench中,分析计算其在径向正弦载荷下衬垫的等效应力、位移、接触应力和等效剪切应力的变化特性;并结合实际服役工况下R44直升机失效的自润滑关节轴承衬垫进行分析。结果表明:在整个周期内,衬垫的边缘因为被挤压而发生变形,衬垫的等效应力和等效变形最大值均出现在外圈的边缘上,接触应力最大值所在的区域始终出现在衬垫的顶部和底部,并且接触应力分布区域的移动与内圈的转动方向一致,切应力最集中的地方在径向载荷施加点的左上方、左下方、右上方、右下方以及左右两侧;由于实际服役工况中载荷的变化,导致衬垫的损伤上半部分是以接触应力引起的疲劳损伤为主,下半部分是以切应力导致的转移膜形成为主。The self-lubricating joint bearings of the R44 helicopter main rotor variable-pitch tie rod ends were taken as the research objects. The rotating and swinging finite element model was established with three-dimensional modeling software Solidworks and applied to the finite element analysis software Ansys Workbench. The change characteristics of equivalent stress, displacement,contact stress and shear stress of the liner under radial sinusoidal load were analyzed and calculated,and the failure of the self-lubricating joint bearing liner of the R44 helicopter under actual service conditions was analyzed. The results showed that during the whole period,the edge of the liner was deformed due to being squeezed, and the equivalent stress and the equivalent maximum deformation of the liner appeared on the edge of the outer ring;the area with the maximum contact stress always appeared at the top and bottom of the liner, and the movement of the contact stress distribution area was consistent with the rotation direction of the inner ring;the most concentrated shear stress was in the upper left, lower left, upper right, lower right,left and right areas of the radial load application point. Due to the change of load in actual service conditions,the damage of liner was mainly caused by fatigue damage arising from contact stress in the upper part and transfer film was caused by shear stress in the lower part.

关 键 词：关节轴承 有限元分析 径向载荷 自润滑衬垫 摩擦磨损 

分 类 号：V258.5[一般工业技术—材料科学与工程] TH117.1[航空宇航科学与技术—航空宇航制造工程]