航空铝合金材料微动疲劳裂纹扩展寿命研究  

Study on Propagation Life of Fretting Fatigue Crack of Aerial Aluminum Alloy

作　　者：杨茂胜[1] 毕玉泉[1] 任剑[1] 王海东[1] 姜文豪[1] 

机构地区：[1]海军航空工程学院青岛校区,山东青岛266041

出　　处：《装备环境工程》2012年第5期1-5,共5页Equipment Environmental Engineering

基　　金：国家自然科学基金(51075394)

摘　　要：以断裂力学为基础,根据复合型裂纹断裂判据建立了LY12CZ铝合金材料微动疲劳裂纹扩展寿命预测模型,确定了模型中的参数,通过预测寿命与试验值的对比验证了该模型的正确、有效性。研究结果表明,微动疲劳裂纹形成阶段比较快,其寿命只占整个疲劳寿命的20%～25%,结构失效所消耗的时间主要在裂纹扩展阶段。A new model for predicting propagation life of fretting fatigue crack of aluminum alloy LY12CZ was established based on part mechanics and part criterion of composite crack.Parameters of the model were determined.The correctness and validity of the model were validated according to the contrast of experiment life and predicting life.The results showed that fretting fatigue crack formation is fast and its propagation life is only 20 to 25 percent of the total fatigue life,which means the failure life of structure is mainly in the propagation phase.

关 键 词：铝合金 微动疲劳 扩展寿命 

分 类 号：V215.6[航空宇航科学与技术—航空宇航推进理论与工程] V236.5