2A12航空铝合金多轴疲劳试验及应力准则寿命预测模型研究

发布时间：2018-04-28 11:38

本文选题：A铝合金 + 多轴疲劳　；参考：《中国机械工程》2017年09期

【摘要】：针对多轴疲劳失效问题,选取2A12航空铝合金进行应力幅比变量、相位差变量和平均应力变量的多轴疲劳试验。对常用的3种多轴疲劳应力准则寿命预测模型(即Lee准则、Carpinteri准则和Sines准则)进行讨论,并通过引入应力幅比参量和相位差参量,提出基于Carpinteri准则的修正模型。将不同条件下2A12航空铝合金的试验寿命与不同应力准则下模型的预测寿命进行比较,结果表明:Lee准则对上述多轴疲劳试验的预测结果过于危险;Carpinteri准则和Sines准则由于未考虑拉-扭应力幅比和相位差因素,预测寿命与实际寿命相比均出现了较大偏差;修正后的应力准则寿命预测模型在不同条件下90%的寿命预测数据在两倍误差带内。
[Abstract]:In view of the multiaxial fatigue failure problem, the multi axis fatigue test of the stress amplitude ratio, phase difference and average stress variable of 2A12 aeronautical aluminum alloy is selected. 3 commonly used multi axis fatigue stress criterion life prediction models (Lee criterion, Carpinteri criterion and Sines criterion) are discussed, and the stress amplitude ratio parameter and phase are introduced. The modified model based on the Carpinteri criterion is proposed. The life of the 2A12 aviation aluminum alloy under different conditions is compared with the predicted life of the model under the different stress criteria under different conditions. The results show that the Lee criterion is too dangerous for the prediction results of the multi axis fatigue test, and the Carpinteri criterion and the Sines criterion have not considered the tensile torsion stress. Compared to the amplitude ratio and phase difference, the predicted life expectancy has a large deviation compared with the actual life span, and the modified stress criterion life prediction model is within two times the error zone of 90% life prediction data under different conditions.

【作者单位】：中国民航大学中欧航空工程师学院;中国南方航空股份有限公司;
【基金】：国家自然科学基金资助项目(11502285) 中央高校基本科研业务费专项资金资助项目(3122016U003)
【分类号】：O346.2;V250.2

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