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FATIGUE LIFE PREDICTION THEORY OF COMPOSITE LAMINATES AND EXPERIMENTAL VERIFICATION

查看全文 作　　者：[1]XiongJunjiang;[1]WuZhe;[1]GaoZhentong;[2]ShenoiRAjiat 高影响力作者 机构地区：[1]AircraftDesignBureau,BeijingUniversityofAeronauticsandAstronautics,Beijing100083,China;[2]UniversityofSouthampton高影响力机构 出　　处：《Chinese Journal of Mechanical Engineering》索引2003年第16卷第2期,共3页高影响力期刊 基　　金：This project is supported by National Natural Science Foundation of China (No.50005003);Aeronautic Science Foundation of China (No.0lA5l0l1) 摘　　要：According to traditional phenomenological fatigue methodology and modern continuum damage mechanics theory, dual fatigue cumulative damage rules to predict fatigue damage formation and propagation lives of the notched composite laminates are presented.A 3-dimensional damage constitutive equation of anisotropic composites is also established.Damage strain energy release rate is interpreted as a driving force of the fatigue delamination damage propagation.A new damage evolution equation and a damage propagation (a-(m-N( surface (stress amplitude-mean stress-life surface) are derived.Hence, using the method above, the fatigue life of composite components can be predicted.Finally, theoretically predicted results are compared with experimental data.It is found that the deviation of theoretic prediction from experimental results is about 22%. 关 键 词：复合层压板 疲劳寿命 预测 检验 累积损伤
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