飞机机翼疲劳断裂过程的有限元分析  

Finite Element Analysis of Aerofoil Fatigue Failure

作　　者：高东宇[1] 林日新 

机构地区：[1]哈尔滨理工大学科研处,黑龙江哈尔滨150080 [2]哈尔滨不锈钢制品厂,黑龙江哈尔滨150001

出　　处：《哈尔滨理工大学学报》2006年第3期18-21,共4页Journal of Harbin University of Science and Technology

摘　　要：重点研究了飞机机翼的疲劳与断裂问题.对机翼疲劳裂纹扩展进行了理论分析.介绍了疲劳断裂过程有限元模拟的几种方法,运用有限元分析软件ABAQUS.对飞机机翼疲劳断裂过程进行了有限元分析,结果表明,在加载条件下,飞机机翼发生疲劳断裂的最危险部位位于机翼根部.Aerofoil fatigue Failure is researched in this paper. Crack propagation of aerofoil is analyzed. methods of finite element analysis of fatigue failure are introduced. ABAQUS is used to simulate aerofoil fatigue The failure. The condition of loading indicates that the worst hazardous area is in airfoil root when fatigue fracture occurs.

关 键 词：有限元 疲劳断裂 裂纹扩展 

分 类 号：O34[理学—固体力学]