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中文摘要：
模拟飞机服役环境,对航空LY12铝合金试验件做了腐蚀试验,然后通过疲劳试验得到LY12铝合金新试验件和预腐蚀试验件的疲劳寿命数据。分析了腐蚀对航空LY12铝合金的影响。通过观测断面腐蚀坑的尺寸,基于初始不连续状态（IDS）建立了把腐蚀坑看做表面裂纹的几种模型,并对几种裂纹模型的疲劳寿命计算结果和实际试验结果进行了对比分析。结果表明：直接把腐蚀坑看做表面裂纹是不合理的,考虑材料初始不连续状态所建立的表面裂纹模型计算结果和试验结果比较吻合;随着腐蚀坑的增大,裂纹模型2更为合理。所以,很难用一个合适的裂纹模型来描述腐蚀坑,只有把腐蚀坑分组才有可能得出更精确的描述。
英文摘要：
Corrosion experiment is performed for aviation LY12 aluminum alloy with imitating service environment of the military airplane. The fatigue life data for both un-corroded and pre-corroded LY12 aluminum alloy specimens are obtained after corrosion damage tests. The corrosion effects on LY12 aluminum are analyzed. Several predictive models are presented to calculate the fatigue life by measured value of pit size,and these predictive models of pit-as-crack are based on the initial discontinuity state （IDS）. The calculated results of several predictive models based on IDS and straight pit-as-crack model are contrasted with experimental date. The results show that the calculated results of predictive models based on IDS agree reasonably with the experiment results,and the pit-as-crack directly is unreasonable. With the increment of pit size,the model 2 is more reasonable. It may be necessary to use different predictive models rather than a single predictive model to describe the corrosion pit.
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