| 国产碳纤维复合材料开孔拉伸失效分析与预测 |
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| 引用本文： | 肖梦丽,张勇波,王治华,傅惠民,杨鑫.国产碳纤维复合材料开孔拉伸失效分析与预测[J].航空动力学报,2015,30(12):2857-2862. |
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| 作者姓名： | 肖梦丽 张勇波 王治华 傅惠民 杨鑫 |
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| 作者单位： | 北京航空航天大学小样本技术研究中心, 北京 100191,北京航空航天大学小样本技术研究中心, 北京 100191,北京航空航天大学小样本技术研究中心, 北京 100191,北京航空航天大学小样本技术研究中心, 北京 100191,北京航空航天大学小样本技术研究中心, 北京 100191 |
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| 基金项目： | 国家自然科学基金(11501022);北京市自然科学基金(3154034) |
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| 摘 要： | 基于国产碳纤维复合材料含孔层合板失效模式和损伤机理研究,结合试验分析建立了符合其失效机理的有限元模型,并在有限元模型中研究了不同失效准则对剩余强度计算结果的影响,通过比较试验数据与数值模拟结果表明:二维模型能比较准确地预测国产碳纤维复合材料含孔层合板的剩余强度,破坏载荷的数值模拟与试验数据的相对误差为7.9%,而拉伸模量的相对误差为5.6%.
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| 关 键 词： | 复合材料层合板 拉伸试验 渐进失效分析 有限元法 剩余强度 |
| 收稿时间： | 5/5/2014 12:00:00 AM |
Failure analysis and prediction on the open-hole tensionof domestic carbon fiber composite |
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| XIAO Meng-li,ZHANG Yong-bo,WANG Zhi-hu,FU Hui-min and YANG Xin.Failure analysis and prediction on the open-hole tensionof domestic carbon fiber composite[J].Journal of Aerospace Power,2015,30(12):2857-2862. |
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| Authors: | XIAO Meng-li ZHANG Yong-bo WANG Zhi-hu FU Hui-min and YANG Xin |
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| Institution: | Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China,Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China,Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China,Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China and Research Center of Small Sample Technology, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | Based on the research of the failure mode and damage mechanism of the notched domestic carbon fiber composite laminates and the experimental analysis, finite element models were established. Then the effect of different failure criterias on the residual strength of notcked domestic carbor fiber composite laminates was studied in the corresponding finite element model. Through the comparison between experimental data and simulation results, it was found that the two-dimensional model could predict the residual strength of the notched domestic carbon fiber composite laminates accurately, the relative error between numerical simulation result and experimental data of failure load was 7.9%,while the relative error of tensile modulus was 5.6%. |
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| Keywords: | composite laminates tension experiment progressive failure analysis finite element method residual strength |
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