A Fatigue Study of C-130 Aircraft Skin Using the Stop Drill Technique
A Fatigue Study of C-130 Aircraft Skin Using the Stop Drill Technique
复制标题
DOI：
10.4028/www.scientific.net/msf.730-732.685
复制
发表时间：
2012-11
期刊：
影响因子：
--
通讯作者：
J. A. Cardoso;V. Infante;B. Serrano
中科院分区：
文献类型：
--
作者：
J. A. Cardoso;V. Infante;B. Serrano
止钻技术是一种简单、经济的方法，通过在裂纹尖端钻孔，减少应力集中，从而延缓裂纹的扩展。本文研究了C-130飞机蒙皮2024-T3铝合金试件的裂纹扩展情况，并研究了停钻直径的增加对裂纹萌生寿命的影响。采用ANSYS Sr和MATLAB Br交互作用的方法对裂纹自动扩展进行了数值模拟，并进行了疲劳试验验证。采用Morrow方程预测了停钻的疲劳寿命。数值计算结果与实验结果在沿着裂纹长度方向上的应力强度因子具有良好的一致性。结果表明，钻头直径越大，疲劳寿命越长。与直径为2 mm的停钻相比，直径为4 mm和6 mm的停钻疲劳寿命分别提高了189%和464%，数值计算结果分别提高了333%和952%。
The stop-drilling technique is a simple and economic way to delay crack propagationby drilling a hole on the crack tip and reducing stress concentration. This paper presents thepropagation of cracks and investigates how the increasing of the stop-drill diameter improvescrack initiation life in specimens of 2024-T3 aluminium alloy of C-130 aircraft skin. A numericalmethod was applied to simulate an automatic crack propagation by interacting ANSYSr andMATLABr, and several experimental fatigue tests were done to support the computationalresults. A Morrow equation was used to predict the fatigue life of the stop-drill. Good agreementof stress intensity factor along crack length was obtained between numerical and experimentalresults. All results show that fatigue life increases when the stop-drill diameter is larger. Whencompared to the 2mm diameter stop-drill, the experimental results show an improvement of189% and 464% to 4mm and 6mm diameter stop-drill fatigue life, and the numerical results of333% and 952%, respectively.