| 复合材料层压板疲劳寿命预测方法 |
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| 引用本文： | 董兴建,李亚智,孟光.复合材料层压板疲劳寿命预测方法[J].上海交通大学学报,2004,38(10):1748-1752. |
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| 作者姓名： | 董兴建 李亚智 孟光 |
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| 作者单位： | 1. 上海交通大学,振动、冲击、噪声国家重点实验室,上海,200030
2. 西北工业大学,飞机结构强度研究所,西安,710072 |
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| 基金项目： | 航空基金资助项目(98B53020) |
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| 摘 要： | 测定了碳纤维／树脂基T300／QY8911复合材料的3组典型单轴循环应力下的S-N曲线．基于试验数据，建立了多轴循环应力作用下单向板的寿命模型，并通过整合平面应力分析、失效分析和材料性质退化模块模拟多向层压板的疲劳失效过程．这种方法试图基于单向板在确定应力比下的疲劳试验结果，预测同种材料体系的任意铺层形式的多向层压板在复杂循环应力作用下的疲劳寿命．对于以分层破坏为主控因素的层压板，基于层间应力的计算结果，用计算面内累计损伤的方法计算分层损伤，层压板的寿命等于分层扩展寿命和分层后子层板剩余寿命之和．考虑分层扩展后，层压板的寿命预测结果得到明显改善．
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| 关 键 词： | 复合材料 层压板 累积损伤 疲劳寿命 分层 |
| 文章编号： | 1006-2467(2004)10-1748-05 |
| 修稿时间： | 2003年9月20日 |
Life Prediction Methodology for Composite Laminates |
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| DONG Xing-jian,LI Ya-zhi,MENG Guang ai ,China, . Inst. of Aircraft Structures,Northwestern Polytechnical Univ.,Xi'an.Life Prediction Methodology for Composite Laminates[J].Journal of Shanghai Jiaotong University,2004,38(10):1748-1752. |
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| Authors: | DONG Xing-jian LI Ya-zhi MENG Guang ai China Inst of Aircraft Structures Northwestern Polytechnical Univ Xi'an |
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| Institution: | DONG Xing-jian~1,LI Ya-zhi~2,MENG Guang~1 ai 200030,China, 2. Inst. of Aircraft Structures,Northwestern Polytechnical Univ.,Xi'an 710072) |
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| Abstract: | Three kinds of fatigue tests at certain stress ratio for unidirection T300/QY8911 Carbon/Bismalimide composite laminates were performed to obtain the S-N curves. Based on the fatigue tests, a cumulative fatigue damage model was presented, which can be used to predict the fatigue life of multidirectional laminates with arbitrary stacking sequence under complicated fatigue loadings. This model is an integration of three major components: stress analysis, failure analysis and material property degradation rules. This can significantly reduce the test costs for laminate structures. If the major model of failure is controlled by fiber fracture or transverse cracking, this model can predict the fatigue life of composite laminates. As to laminates with delamination failure mode, a three-dimentional finite element method was developed in order to get full stress state in the vicinity of free edges and a simplified model was developed for evaluation fatigue life of this kind of composite laminate. |
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| Keywords: | composite laminate cumulative damage fatigue life delamination |
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