| 含冲击损伤复合材料层合板疲劳试验研究 |
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| 引用本文： | 徐颖%温卫东%崔海坡.含冲击损伤复合材料层合板疲劳试验研究[J].宇航材料工艺,2007,37(2):73-76,80. |
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| 作者姓名： | 徐颖%温卫东%崔海坡 |
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| 作者单位： | 南京航空航天大学能源与动力学院,南京,210016 |
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| 摘 要： | 针对两种不同铺层顺序的T300／BMP316复合材料层合板，进行了低速冲击后不同应力水平下的等幅拉一拉疲劳试验。结果表明：低速冲击后，材料疲劳寿命的对数与应力水平成线性关系；在低应力水平下，层合板的主要疲劳损伤模式为分层，而在高应力水平下，其主要疲劳损伤模式为纤维断裂；随着疲劳应力水平的降低，层合板内损伤面积增加且刚度退化幅度变大。
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| 关 键 词： | 疲劳 低速冲击 复合材料层合板 |
| 修稿时间： | 2006-03-20 |
Fatigue Testing of Impact-Damaged Composite Laminates |
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| Xu Ying,Wen Weidong,Cui Haipo.Fatigue Testing of Impact-Damaged Composite Laminates[J].Aerospace Materials & Technology,2007,37(2):73-76,80. |
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| Authors: | Xu Ying Wen Weidong Cui Haipo |
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| Institution: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016 |
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| Abstract: | Fatigue testing of 3300/BMP316 laminates with two ply stacking sequences is performed in constant amplitude tension-tension loading at various stress levels. The linear relationship between the stress level and fatigue life is obtained for all laminates with impact damage. At lower stress level, the main damage in fatigue failed specimens is delamination, and at higher stress level, the main damage is fiber failure. The damage area and stiffness degradation of specimen are increased with the decrease of stress level. |
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| Keywords: | Fatigue Low velocity impact Composite laminates |
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