摘要
根据已有的飞机结构主体材料LY12CZ试验数据,基于疲劳缺口系数的定义式计算了3种腐蚀年限试件的疲劳缺口系数。运用场强法模型计算了疲劳缺口系数并拟合了其与缺口半径的关系式。采用当量化处理的方法,将3种不同腐蚀年限结构件的腐蚀坑当量为3种半径的半圆形缺口,设计疲劳试验进行验证,试验结果与已有的疲劳试验数据吻合得较好。
The fatigue notch factor of the test pieces of three different corrosion years was calculated based on LY12CZ aluminum alloy test data and the definition of fatigue notch factor.Fatigue notch factor was calculated using field intensity method and its relationship with the notch radius was fitted.The corrosion pits of three corrosion years were treated to equivalents of three semi-circle notches of different radius and a fatigue test was designed to verify it.The experimental results agreed well with the foregoing test data;indicated that the method is reasonable.
出处
《装备环境工程》
CAS
2010年第6期130-133,156,共5页
Equipment Environmental Engineering
关键词
腐蚀坑
疲劳缺口系数
场强法
当量化
corrosion pit
fatigue notch factor
field intensity method
equivalent
