Study on Bending Properties of Honeycomb Sandwich Materials with Debonding Damage under Hygrothermal Environment
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摘要: 通过使用三明治夹芯等效理论将蜂窝芯层等效为均匀连续的实体单元，将湿热环境中的湿应力等效为热应力，建立湿热环境下的蜂窝夹芯材料本构方程，以改进Hashin准则与Besant准则作为蜂窝夹芯材料的失效判据，并通过编写VUMAT子程序实现。采用Cohesive单元模拟面板与芯层间的连接方式建立湿热环境下蜂窝夹芯板的有限元模型，研究湿热环境对蜂窝夹芯材料弯曲性能的影响。切除某些Cohesive区域模拟面板与芯层脱粘现象并计算脱粘损伤对材料性能的影响，对比边缘脱粘与内部脱粘研究脱粘位置对蜂窝夹芯材料弯曲性能的影响。结果表明湿热环境降低了材料的极限承载能力，脱粘现象会加速面板与芯层分离，脱粘位置影响材料的损伤扩展性能，降低材料的弯曲强度。Abstract: Honeycomb core layer was assumed as a uniform entity in terms of the sandwich equivalent theory, the wet stress in hygrothermal environment is equivalent to the thermal stress, and the constitutive equation of honeycomb sandwich material under hygrothermal environment was established, the improved Hashin criteria and Besant criterion were used as the failure criterion of honeycomb sandwich material, which was realized with VUMAT subroutine. The Cohesive element simulation panel and connection between the core layer to establish finite element model for honeycomb sandwich plates under hygrothermal environment, hygrothermal environment will affect the bending performance of the honeycomb sandwich materials. By removing debonding phenomena between the Cohesive zone model panel and the core layer, the effect of the debonding damage on the properties of materials is calculated, the effect of the debonding location the bending performance of the honeycomb sandwich materials between the edge debonding and the internal debonding is compared. The results show that the hygrothermal environment reduces the ultimate bearing capacity of the material, the debonding phenomenon accelerates the separation of the panel and the core layer, the debonding position affects the damage spreading property and reduce the bending strength of the material.
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表 1 蜂窝面板参数退化
损伤类型 材料参数退化方式 基体拉伸损伤 E22=0.2E22, G12=0.2G12, G23=0.2G23 基体压缩损伤 E22=0.4E22, G12=0.4G12, G23=0.4G23 纤维拉伸损伤 Eii=0.07Eii, Gij=0.07Gij, υij=0.07υij(i, j=1, 2, 3, i≠j) 纤维压缩损伤 Eii=0.14Eii(i=1, 2, 3), Gij=0.14Gij, υij=0.14υij(i, j=1, 2, 3, i≠j) 纤维基体剪切损伤 G12=0.1G12, υ12=0.1υ12 分层损伤 E33=0.1E33, G23=0.1G23, υ23=0.1υ23, υ13=0.1υ13 
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表 2 蜂窝芯层参数退化
损伤状态 参数退化 Fcore2≥1, 材料发生皱曲破坏 E1=0.4E1, E2=0.4E2, E3=0.45E3
υ12=υ12, υ13=υ13, υ23=υ23
G12=0.4G12, G13=0.4G13, G23=0.4G23
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