| 拉伸载荷下贴补复合材料层合板的渐进损伤分析 |
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| 引用本文： | 相超,周丽,宋恩鹏,叶正浩,许希武.拉伸载荷下贴补复合材料层合板的渐进损伤分析[J].工程力学,2014,31(10):234-241. |
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| 作者姓名： | 相超 周丽 宋恩鹏 叶正浩 许希武 |
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| 作者单位： | 1.南京航空航天大学机械结构力学及控制国家重点实验室,南京 210016; |
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| 基金项目： | 国家自然科学基金项目(11172128);国家自然科学基金国际(地区)合作与交流项目(61161120323);高等学校博士学科点专项科研基金项目(20123218110001);江苏省“六大人才高峰”项目(2010-JZ-004);江苏高校优势学科建设工程项目 |
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| 摘 要： | 基于连续介质损伤力学和粘聚区模型建立了贴补复合材料层合板的渐进损伤分析模型,计算了拉伸载荷下修补结构的极限强度。数值仿真结果和实验结果吻合较好,验证了该模型的有效性。基于建立的模型研究了贴补复合材料层合板的损伤演化过程,并讨论了补片参数对修补结构拉伸性能的影响。研究结果表明:补片参数对贴补复合材料层合板的破坏模式与损伤演化过程有显著影响;不同破坏模式下,补片参数的改变对修补结构极限强度的影响效果不同。研究结果可为复合材料层合板的贴补设计提供部分理论参考。
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| 关 键 词： | 复合材料 贴补修理 有限元法 连续介质损伤力学 粘聚区模型 渐进损伤分析 |
| 收稿时间： | 2013-04-19 |
PROGRESSIVE DAMAGE ANALYSIS OF BONDING PATCH-REPAIRED COMPOSITE LAMINATES UNDER TENSION LOADING |
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| Affiliation: | 1.State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;2.Shenyang Aircraft Design Institute, Shenyang 110035, China |
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| Abstract: | A progressive damage analysis model based on the continuum damage mechanism and cohesive zone model is developed for composite laminates repaired with bonding patches. The ultimate strength of repaired structures under tension loading is calculated with the developed model. Simulation results agree well with experimental results, which proves the validity of the analysis model. The damage evolution process and influence of patch parameters on the tensile behaviour of repaired structures are also analysed. The results show that patch parameters influence the failure mode and damage evolution process of repaired structures and that strength increase is not constant in different failure modes when patch parameters change. The results of this study can provide some references for the design of bonding patch repairs for composite laminates. |
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