| FATIGUE LIFE PREDICTION THEORY OF COMPOSITE LAMINATES AND EXPERIMENTAL VERIFICATION |
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| 引用本文： | Xiong JunjiangWu ZheGao ZhentongAircraft Design Bureau,Beijing University of Aeronauticsand Astronautics,Beijing 100083,ChinaShenoi R AjiatUniversity of Southampton. FATIGUE LIFE PREDICTION THEORY OF COMPOSITE LAMINATES AND EXPERIMENTAL VERIFICATION[J]. 机械工程学报(英文版), 2003, 16(2): 178-180 |
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| 作者姓名： | Xiong JunjiangWu ZheGao ZhentongAircraft Design Bureau Beijing University of Aeronauticsand Astronautics Beijing 100083 ChinaShenoi R AjiatUniversity of Southampton |
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| 作者单位： | Xiong JunjiangWu ZheGao ZhentongAircraft Design Bureau，Beijing University of Aeronauticsand Astronautics，Beijing 100083，ChinaShenoi R AjiatUniversity of Southampton |
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| 基金项目： | This project is supported by National Natural Science Foundation of China (No.50005003)，Aeronautic Science Foundation of China (No.0lA5l0l1) |
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| 摘 要： | According to traditional phenomenological fatigue methodology and modem 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 σa-σm-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%.
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| 关 键 词： | 复合层压板 疲劳寿命 预测 检验 累积损伤 |
FATIGUE LIFE PREDICTION THEORY OF COMPOSITE LAMINATES AND EXPERIMENTAL VERIFICATION |
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| XiongJunjiang WuZhe GaoZhentong ShenoiRAjiat. FATIGUE LIFE PREDICTION THEORY OF COMPOSITE LAMINATES AND EXPERIMENTAL VERIFICATION[J]. Chinese Journal of Mechanical Engineering, 2003, 16(2): 178-180 |
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| Authors: | XiongJunjiang WuZhe GaoZhentong ShenoiRAjiat |
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| Affiliation: | [1]AircraftDesignBureau,BeijingUniversityofAeronauticsandAstronautics,Beijing100083,China [2]UniversityofSouthampton,BeijingUniversityofAeronauticsandAstronautics,Beijing100083,China |
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| Abstract: | 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%. |
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| Keywords: | Fatigue Life prediction Composite laminates Damage evolution |
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