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程小全 杨琨 胡仁伟 邹健. 缝合复合材料层合板拉伸疲劳损伤及其机理[J]. 力学学报, 2010, 42(1): 132-137. DOI: 10.6052/0459-1879-2010-1-2009-028
引用本文: 程小全 杨琨 胡仁伟 邹健. 缝合复合材料层合板拉伸疲劳损伤及其机理[J]. 力学学报, 2010, 42(1): 132-137. DOI: 10.6052/0459-1879-2010-1-2009-028
Xiaoquan Cheng, Kun Yang, Renwei Hu, Jian Zou. Tensile fatigue damage and its mechanism of stitched composite laminates[J]. Chinese Journal of Theoretical and Applied Mechanics, 2010, 42(1): 132-137. DOI: 10.6052/0459-1879-2010-1-2009-028
Citation: Xiaoquan Cheng, Kun Yang, Renwei Hu, Jian Zou. Tensile fatigue damage and its mechanism of stitched composite laminates[J]. Chinese Journal of Theoretical and Applied Mechanics, 2010, 42(1): 132-137. DOI: 10.6052/0459-1879-2010-1-2009-028

缝合复合材料层合板拉伸疲劳损伤及其机理

Tensile fatigue damage and its mechanism of stitched composite laminates

  • 摘要: 对有、无缝合复合材料层合板的拉伸疲劳性能进行了试验研究,考察了0^\circ缝合对复合材料光滑板拉伸疲劳损伤扩展规律的影响. 通过有限元素法分析了有、无缝合复合材料层合板的应力状态分布情况,对缝合复合材料层合板的拉伸疲劳损伤及其扩展机理进行了分析. 研究表明,缝合改变了复合材料层合板拉伸疲劳损伤起始与扩展的机理,针脚附近的面内正应力\sigma_x与层间剪应力的集中对层合板拉伸疲劳损伤的发生与扩展有着重要的作用,自由边界处的层间集中应力对缝合板的疲劳性能也有影响. 自由边界处的层间集中应力是导致无缝合层合板疲劳损伤及其扩展的主要原因.

     

    Abstract: Stitched laminate is a new kind of composite structure toimprove the interface strength of composite. But the in-plane properties ofthe laminate may reduce because there are local fiber bending in thelaminate plane and in the thickness direction, and the damage induced by thestitching threads. A lot of researches have been carried out on theproperties of laminates to push this material into engineering applications,such as in-plane tension and compression, compression after impact,hygrothermal properties, etc. But few studies have been performed onstitched composite fatigue properties. The aim of this paper is tocomprehend the fatigue damage development and mechanism of stitchedlaminates under tensile loads. The material of the laminates was uni-weaveT300/QY9512 stitched in 0^\circ direction. Un-stitched laminates were studiedfor comparison with the stitched laminates.Experimental study was carried out on the fatigue performance of stitchedand non-stitched composite laminate. The finite element models wereestablished to obtain the stress or strain distributions in the laminates.The mechanism of tensile fatigue damage origination and propagation ofstitched laminates was analyzed. The results show that the tensile fatiguedamage origination and propagation mechanisms of laminates have been changedby stitching. The stress concentration of in-plane stress \sigma_x andinterlaminar shear stress near the stitching node plays an important role indamage origination and propagation. Stress concentration of interlaminarstress at the free sides has effect on fatigue performance of stitchedlaminates. The stress concentration of interlaminar stress at the free sidesis the main reason that causes fatigue damage and its propagation ofnon-stitched laminates.

     

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