整体壁板三维裂纹应力强度因子计算与分析  

Research and Analysis on Methods of Three-dimensional Crack Stress Intensity Factor for Integral Panel

作　　者：闫晓中[1] 王生楠[1] 苏毅[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空工程进展》2011年第2期205-209,共5页Advances in Aeronautical Science and Engineering

摘　　要：近年来,整体壁板成为飞机结构设计上一个新的研究方向。针对典型的飞机整体壁板,应用有限元软件ABAQUS建立了含裂纹整体壁板的参数化模型,对裂纹在凸台和筋条中的扩展轨迹进行三维裂纹扩展模拟。分析了裂纹在扩展过程中,凸台、筋条、蒙皮中裂纹应力强度因子的变化情况以及凸台、筋条的止裂性能。研究结果对整体壁板的损伤容限设计和评定具有一定的指导意义。In resent years,integrally stiffened panel has already been a new research direction in aircraft structure design.For a typical integral panel of aircraft,the parameters model of the panel with cracks is established.Three dimensional crack growth trajectories in the skin pad and the stiffener are then simulated.Changes of the stress intensity factor in the skin,the pad and the stiffener,as cracks grow,are analyzed by use of finite element method.The conclusions drawn in this paper can be used for damage tolerance design and assessment of the integral panel of aircraft.

关 键 词：整体壁板 裂纹扩展 ABAQUS 应力强度因子 

分 类 号：V214.5[航空宇航科学与技术—航空宇航推进理论与工程]