FATIGUE LIFE PREDICTION THEORY OF COMPOSITE LAMINATES AND EXPERIMENTAL VERIFICATION  

作　　者：XiongJunjiang WuZhe GaoZhentong ShenoiRAjiat 

机构地区：[1]AircraftDesignBureau,BeijingUniversityofAeronauticsandAstronautics,Beijing100083,China [2]UniversityofSouthampton

出　　处：《Chinese Journal of Mechanical Engineering》2003年第2期178-180,共3页中国机械工程学报（英文版）

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 moderncontinuum damage mechanics theory, dual fatigue cumulative damage rules to predict fatigue damageformation and propagation lives of the notched composite laminates are presented. A 3-dimensionaldamage constitutive equation of anisotropic composites is also established. Damage strain energyrelease rate is interpreted as a driving force of the fatigue delamination damage propagation. A newdamage evolution equation and a damage propagation σ_a-σ_m-N~* surface (stress amplitude-meanstress-life surface) are derived. Hence, using the method above, the fatigue life of compositecomponents can be predicted. Finally, theoretically predicted results are compared with experimentaldata. It is found that the deviation of theoretic prediction from experimental results is about22%.According to traditional phenomenological fatigue methodology and moderncontinuum damage mechanics theory, dual fatigue cumulative damage rules to predict fatigue damageformation and propagation lives of the notched composite laminates are presented. A 3-dimensionaldamage constitutive equation of anisotropic composites is also established. Damage strain energyrelease rate is interpreted as a driving force of the fatigue delamination damage propagation. A newdamage evolution equation and a damage propagation σ_a-σ_m-N~* surface (stress amplitude-meanstress-life surface) are derived. Hence, using the method above, the fatigue life of compositecomponents can be predicted. Finally, theoretically predicted results are compared with experimentaldata. It is found that the deviation of theoretic prediction from experimental results is about22%.

关 键 词：FATIGUE life prediction composite laminates damage evolution 

分 类 号：TB33[一般工业技术—材料科学与工程] O346.2[理学—固体力学]