文档介绍：第 42 卷第 3 期南京航空航天大学学报 Vo l. 42 N o. 3
2010 年 6 月 Journal of Nanjing U niversity of Aero nautics & Astronautics Jun. 2010
含多裂纹铝板的剩余强度评估
徐武1 张晓晶2 汪海2 汤超2
( 1. 上海交通大学船舶海洋与建筑工程学院, 上海, 200240; 2. 上海交通大学航空航天学院, 上海, 200240)
摘要: 提出了一种计算飞机多裂纹平板结构剩余强度的方法。该方法采用多裂纹结构中主裂纹旁的小裂纹的张
开位移来预测剩余强度。裂尖张开位移和剩余强度通过应用弹塑性有限元获得。采用已发表的实验来应用和验
证这个方法, 结果表明: 本模型预测的剩余强度与实验值相比误差在 10% 之内。
关键词: 多裂纹; 剩余强度; 裂纹张开位移; 弹塑性有限元
中图分类号: V 215. 6 文献标识码: A 文章编号: 1005-2615( 2010) 03-0330-05
Residual Strength Prediction of Thin Aluminum Alloy Panels with
Multiple Site Cracks
X u W u1 , Zhang X iaoj ing2 , W ang H ai 2, Tang Chao2
( 1. Scho ol of N av al A rchitecture, Ocean and Civ il Eng ineering, Shang hai
Jiao T o ng U niv ersit y, Shang hai, 200240, China;
2. Schoo l o f A ero na ut ics a nd A st ro nautics, Shang hai Jiao T o ng U niv ersit y, Shang hai, 200240, China)
Abstract: A method is pr opo sed to predict the residual str ength of the aircraft str ucture w ith multiple
site cracks. The m ethod is based on the crack tip opening displacement ( CTOD) of the small crack
clo sed to the leading cr ack. The CTOD and the residual strength ar e obtained by perform ing elastic-plas-
tic finite elem ent analysis. T he exper im ent fr om the open liter ature is used fo r the application and the
verification of the m ethod. T he relative err or betw een the predictio n and the exper im ent i