含孔复合材料层合板疲劳寿命预测研究 |
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引用本文: | 齐红宇,温卫东,崔海涛.含孔复合材料层合板疲劳寿命预测研究[J].航空动力学报,2003,18(5):658-661. |
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作者姓名: | 齐红宇 温卫东 崔海涛 |
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作者单位: | 1.南京航空航天大学能源与动力学院,江苏南京210016 |
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基金项目: | 航空发动机结构强度"九五"项目预研课题(24.8.1.26) |
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摘 要: | 运用损伤力学理论,从应变等效性假设出发,基于复合材料结构"点应力"准则的概念,提出了一种考虑残余应变影响的刚度下降疲劳损伤模型。以我国新近研制的高性能复合材料T300/KH304为研究对象,采用该模型预测了带有孔径为5mm层合板的疲劳寿命并对模型的合理性进行了实验验证,从不同应力水平的疲劳试验的结果可以看出,其最大相对误差为12.2%。
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关 键 词: | 航空、航天推进系统 疲劳寿命 复合材料 残余应变 刚度下降 |
文章编号: | 1000-8055(2003)05-0658-04 |
收稿时间: | 2002/11/18 0:00:00 |
修稿时间: | 2002年11月18 |
Fatigue Life Predication of Notched Composite Material Laminates |
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Institution: | 1.Beijing University of Aeronautics and Astronautics,Beijing 100083,China2.Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China |
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Abstract: | Based on damage theory and strain equivalent hypothesis,a fatigue model is presented in which the residual strain and stiffness degradation are included.A high capability composite material 300/KH304 developed recently is studied in this paper.Using this model,the fatigue life of these laminates with 5 mm holes is predicated.At the same time the fatigue tests are carried out under different stress levels.Compared with the result,the relative tolerance is less than 12.2%. |
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Keywords: | aerospace propulsion system fatigue life composite material residual strain stiffness degradation |
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