| FATIGUE LIFE PREDICTION THEORY OF COMPOSITE LAMINATES AND EXPERIMENTAL VERIFICATION |
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| 作者姓名： | Xiong Junjiang
Wu Zhe
Gao Zhentong
Aircraft Design Bureau Beijing University of Aeronautics
and Astronautics Beijing China
Shenoi R Ajiat
University of Southampton |
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| 作者单位： | Xiong Junjiang
Wu Zhe
Gao Zhentong
Aircraft Design Bureau，Beijing University of Aeronautics
and Astronautics，Beijing 100083，China
Shenoi R Ajiat
University 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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| Xiong Junjiang
Wu Zhe
Gao Zhentong
Aircraft Design Bureau,Beijing University of Aeronautics
and Astronautics,Beijing ,China
Shenoi R Ajiat
University of Southampton.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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