机身某部位连接区疲劳和损伤容限分析  

Analysis of Fatigue and Damage Tolerance of Joint Region of Aircraft Certain Part

作　　者：苏毅[1] 王生楠[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《航空计算技术》2013年第3期45-47,51,共4页Aeronautical Computing Technique

摘　　要：从疲劳和损伤容限的概念出发,对某机身13长桁的框腹板进行受力情况、疲劳寿命、裂纹扩展寿命和剩余强度分析,充分讨论了与框腹板相连的接头的可靠性。在考虑精度的情况下用子模型的方式节省了很多计算时间,用扩展有限元法预测裂纹扩展的轨迹也与实验相吻合,为工程应用提供了简洁有效的途径。Based on the concept of fatigue and damage tolerance,the force,fatigue life,crack growth life and residue strength of web of the 13th truss were analyzed in this paper.The reliability of joint was also discussed.Submodel saved lots of time with considering precision of the calculation.The crack growth track predicted by XFEM agreed well with the experimental results,and this provided a new concision and effective method for the engineering application.

关 键 词：疲劳寿命 裂纹扩展寿命 剩余强度 扩展有限元 

分 类 号：O346.1[理学—固体力学]