| 飞机复合材料长桁压损失效的渐进损伤分析 |
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| 引用本文： | 郑双,何续斌,贾大炜.飞机复合材料长桁压损失效的渐进损伤分析[J].航空计算技术,2016(1). |
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| 作者姓名： | 郑双 何续斌 贾大炜 |
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| 作者单位： | 中航沈飞民用飞机有限责任公司,辽宁 沈阳,110000 |
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| 摘 要： | 针对碳纤维增强树脂基复合材料长桁的压损失效，提出了一种以渐进损伤理论为基础的有限元数值模拟方法。以较常见截面的长桁为分析对象，建立了有限元模型。选用合理的材料受损后的刚度折减方案，基于Hashin失效判断准则，利用ABAQUS软件进行非线性求解后得到了长桁压损失效临界载荷。相应地，制造了3种不同尺寸的T型长桁进行压损试验。对比载荷位移曲线和结构失效临界载荷，结果显示，以渐进损伤理论为基础的有限元数值模拟方法与试验比较吻合。
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| 关 键 词： | 纤维增强复合材料 长桁 渐进损伤 压损 有限元模型 |
Progressive Damage Analysis for Crippling Failure of Aircraft Composite Stringer |
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| Abstract: | A finite element numerical simulation method, based on progressive damage theory, was pro-posed to predict and analyze the crippling failure of fiber-reinforced composite stringers. A finite element model of stringer was established. According to Hashin′s criterion,the crippling critical loads were calcu-lated by using nonlinear solution of ABAQUS baqus software. At the same time,three kinds of of T section stringer with different sizes was manufactured and tested. Compared the numerical results predict by using progressive damage model with the experimental results. The FEM analysis results agree well with the tes-ting results. |
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| Keywords: | fiber-reinforced composite stringer progressive damage crippling finite element model |
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