含表面划伤平纹编织面板蜂窝夹芯结构侧向压缩渐进失效分析
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摘要
为研究表面划伤对平纹编织面板蜂窝夹芯结构侧压性能的影响,建立平纹编织面板蜂窝夹芯结构的渐进失效分析模型。考虑模型具有高度的材料非线性问题,选用ABAQUS/Explicit求解器进行蜂窝夹芯结构的准静态侧向压缩模拟,通过编写VUMAT子程序,分别设置面板和芯子的失效准则以及刚度退化模型,选用内聚力模型模拟胶层,完成含表面划伤的平纹编织面板蜂窝夹芯结构的侧向压缩渐进失效分析,与试验结果相比,破坏强度和失效模式非常吻合。研究结果表明:失效时无损伤一侧面板会产生屈曲行为,使得蜂窝芯面外应力增大,导致蜂窝芯出现损伤。含表面划伤一侧面板会发生经向纤维压缩失效及纤维-基体经向剪切失效,且失效会沿划伤方向从划伤区域附近向两侧扩展。
The progressive damage analysis model of honeycomb sandwich structure with plain braided panel is established. The lateral strength and failure mode of honeycomb sandwich structure with scratch damage on one side panel are studied. The results are compared with the experiments to verify the correctness of the model. Considering the high material nonlinearity of the model, ABAQUS/Explicit solver is used to simulate the quasi-static lateral compression of honeycomb sandwich structure. By compiling VUMAT subroutine, failure criteria and stiffness degradation models of panel and core are set respectively, and cohesion model is used to simulate the adhesive layer to complete progressive damage analysis of honeycomb sandwich structure subjected to lateral compression. The results show that the buckling behavior of the unilateral plate without damage will occur when the failure occurs, which will increase the stress outside the honeycomb core surface and lead to the damage of the honeycomb core. The longitudinal compression failure of fiber and the longitudinal shear failure of the fiber-matrix will occur on one side plate with surface scratches, and the failure will extend from the vicinity of the scratch area to both sides along the scratch direction.
The progressive damage analysis model of honeycomb sandwich structure with plain braided panel is established. The lateral strength and failure mode of honeycomb sandwich structure with scratch damage on one side panel are studied. The results are compared with the experiments to verify the correctness of the model. Considering the high material nonlinearity of the model, ABAQUS/Explicit solver is used to simulate the quasi-static lateral compression of honeycomb sandwich structure. By compiling VUMAT subroutine, failure criteria and stiffness degradation models of panel and core are set respectively, and cohesion model is used to simulate the adhesive layer to complete progressive damage analysis of honeycomb sandwich structure subjected to lateral compression. The results show that the buckling behavior of the unilateral plate without damage will occur when the failure occurs, which will increase the stress outside the honeycomb core surface and lead to the damage of the honeycomb core. The longitudinal compression failure of fiber and the longitudinal shear failure of the fiber-matrix will occur on one side plate with surface scratches, and the failure will extend from the vicinity of the scratch area to both sides along the scratch direction.
引文
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[2] Zabihpoor M,Adibnazari S,Moslemian R,et al.Mechanisms of fatigue damage in foam core sandwich composites with unsymmetrical carbon/glass face sheets[J].Journal of Reinforced Plastics and Composites,2007,26(17):1831-1842.
[3] 郑吉良,孙勇,彭明军.等腰梯形蜂窝芯玻璃钢夹芯板的面内压缩性能[J].复合材料学报,2016,33(2):408-417.
[4] Wang A J,Mcdowell D L.In-plane stiffness and yield strength of periodic metal honeycombs[J].Journal of Engineering Materials & Technology,2004,126(2):137-155.
[5] Lei H,Yao K,Wen W,et al.Experimental and numerical investigation on the crushing behavior of sandwich composite under edgewise compression loading[J].Composites Part B Engineering,2016,94:34-43.
[6] Wang Z,Li Z,Zhou W,et al.On the influence of structural defects for honeycomb structure[J].Composites Part B:Engineering,2018,142:183-192.
[7] 王凯伦,黎增山,郭俊,等.薄蜂窝复合材料夹芯结构侧压性能研究[J].科学技术与工程,2014,14(34):111-116.
[8] 王轩,曹阳丽,邓云飞,等.平纹编织面板蜂窝夹芯结构侧压性能研究[J].玻璃钢/复合材料,2018(8):5-11.
[9] Bora M O,Coban O,Sinmazcelik T.Effect of fiber orientation on scratch resistance in unidirectional carbon-fiber-reinforced polymer matrix composites[J].Journal of Reinforced Plastics and Composite,2010,29:1476-1490.
[10] Seyedmohammad S S,Rani F E.Effects of scratch damage on progressive failure of laminated carbon fiber/epoxy composites[J].International Journal of Mechanical Sciences,2013,67:70-77.
[11] Derek R P,Rani F E,Bashar A K.On the tension strength of carbon/epoxy composites in the presence of deep scratches[J].Engineering Fracture Mechanics,2012,90:30-40.
[12] Xu X,Wisnom M R,Li X,et al.A numerical investigation into size effects in centre-notched quasi-isotropic carbon/epoxy laminates[J].Composites Science and Technology,2015,111:32-39.
[13] Xu X,Wisnom M R,Mahadik Y,et al.An experimental investigation into size effects in quasi-isotropic carbon/epoxy laminates with sharp and blunt notches[J].Composites Science and Technology,2014,100:220-227.
[14] Joel S,Christophe B,Bruno C,et al.Experimental and numerical analysis of carbon fiber reinforced polymer notched coupons under tensile loading[J].Composite Structures,2017,181:145-157.
[15] 杨莹.含孔织物复合材料的强度预测与优化方法研究[D].南京:南京航空航天大学,2009.
[16] 王娟,施建伟,张书亭,等.复合材料螺栓连接接头渐进损伤分析研究进展[J].航空制造技术,2016(3):85-89.
[17] 张阿樱,张东兴.含孔隙碳纤维/环氧树脂层合板力学性能模拟[J].哈尔滨工程大学学报,2013,34(3):389-393.
[18] 华洲.复合材料蜂窝夹芯板结构损伤及其修理后仿真分析[D].哈尔滨:哈尔滨工业大学,2017.
[19] 乔玉,周光明,刘伟先,等.复合材料阶梯形胶接接头渐进损伤分析[J].南京航空航天大学学报,2014,46(4):632-637.