某型号机轮轮毂的疲劳全寿命分析  

Fatigue life analysis for Certain Type of Aircraft Wheel Hub

作　　者：刘文胜[1] 肖彦荣 马运柱[1] 杨肃[1] 

机构地区：[1]中南大学粉末冶金国家重点实验室,长沙410083

出　　处：《航空精密制造技术》2015年第4期13-17,52,共6页Aviation Precision Manufacturing Technology

基　　金：国家高技术研究发展计划(863重点计划)资助项目(2009AA034300)

摘　　要：根据某型号轮毂的强度分析结果,对该型号轮毂进行疲劳损伤分析和损伤容限分析,得到其裂纹生成寿命和裂纹扩展寿命。运用Workbench对轮毂的所有载荷工况进行有限元强度分析和疲劳损伤分析,将运用损伤累积理论计算结果与仿真结果进行对比;对产生初始裂纹的轮毂进行损伤容限分析,得到其裂纹扩展寿命。结果表明,该型号机轮轮毂的疲劳危险部位为胎圈座,轮毂疲劳寿命满足设计要求,损伤的理论计算值和仿真结果偏差很小。Based on the strength analysis result, the fatigue damage and damage tolerance of certain type of wheel hub were analyzed to get the crack formation life and crack propagation life. The strength and fatigue damage of the wheel hub under all load cases with finite element method were analyzed by using Workbench. The damage accumulation theory calculation result was compared with the simulation results. The crack propagation life of the wheel hub was obtained by the damage tolerance analysis of the wheel hub with initial crack. The result shows that the fatigue dangerous part of the wheel damage of theory calculation hub is bead seat. The fatigue life of the wheel hub meets the design requirements. The value is close to the simulation results.

关 键 词：飞机轮毂 疲劳寿命 损伤容限 WORKBENCH NASGRO 

分 类 号：V226.6[航空宇航科学与技术—飞行器设计]