摘要
针对应用于航空重载传动的面齿轮寿命难以预测,分析其裂纹萌生和扩展过程以及相应的寿命.根据材料应变-寿命关系,利用MSC.Fatigue进行裂纹萌生仿真,分析不同负载扭矩、表面粗糙度、表面处理工艺下裂纹萌生寿命的变化规律;根据线性断裂力学理论,借助于Franc3D模拟裂纹扩展过程,直至满足断裂准则,由应力强度因子历程确定裂纹扩展寿命.最终获得面齿轮在不同表面粗糙度、表面处理工艺下的疲劳寿命曲线,实现面齿轮疲劳寿命的预测.
Aiming at that life of face gear used in the aero heavyload condition is difficult to predict, it＇ s necessary to analyze the processes and lives of crack initiation and propagation. Using strainlife relation ship and MSC. Fatigue, the simulation of crack initiation life was in progress to analyze the trend of different load torques, surface roughnesses and surface treatments; according to the theory of linear fracture mechanics, the process of crack propagation was simulated using Franc3D until meeting the fracture criterion and the crack propagation life was calculated on the basis of stress intensity factor. Finally, fatigue life curves of face gear at different surface roughnesses and surface treatments were obtained, which can be used to predict fatigue life of face gear.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2014年第2期148-153,共6页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家高技术研究发展计划资助项目(SS2012AA040104)
关键词
面齿轮
疲劳
寿命
裂纹萌生
裂纹扩展
face gear
fatigue
life cycle
crack initiation
crack propagation
