平纹编织面板蜂窝夹芯结构平拉性能研究

Study on the flatwise tensile properties of honeycomb sandwich structure with plain weave faceplate

为了研究平纹编织面板蜂窝夹芯结构的平拉性能,利用有限元分析软件ABAQUS建立基于渐进损伤失效分析方法的夹芯结构细节模型,选用内聚力模型模拟面板与芯子间的胶层,运用FORTRAN语言编写描述失效和退化准则的USDFLD子程序,对夹芯结构的平拉性能进行预测。结果表明:预测得到的平拉强度和破坏模式与试验结果一致,验证了所建模型正确;面板各层间和面芯之间胶层没有出现损伤;蜂窝芯以蜂窝壁纵向破坏为主,蜂窝芯中部首先出现损伤,随后损伤向两侧扩展,最终整个蜂窝芯中部裂开导致结构失效;面板各层间和面芯之间胶层的剥离强度要高于蜂窝芯厚度方向上的拉伸强度;整个夹芯结构的变形以蜂窝芯厚度方向上的变形为主。

To investigate the flatwise tensile strength of the plain weave panels honeycomb sandwich structure, ABAQUS was used to create a detailed model of the sandwich structure based on the progressive damage failure analysis methodology. The cohesion model was selected to simulate the adhesive layer between the faceplate and the honeycomb core. FORTRAN language was applied to write USDFLD subroutines describing failure and degradation criteria, which predict the flatwise tensile properties of the sandwich structure. The results show that the predicted flatwise tensile strength and failure mode are consistent with the test results, checking whether the model is correct. There is no damage between the layers of the faceplate and the adhesive layer between the faceplate-core. The honeycomb damage is mainly caused by longitudinal damage to the honeycomb wall. Damage occurs first in the middle of the core wall, then the damage spreads to both sides. Finally, the middle part of the whole honeycomb core cracks and the structure fails. The peel strengths of the layers of the faceplate and the adhesive layer between the faceplate-core are higher than the tensile strength in the longitudinal direction of the core. The deformation of the entire sandwich structure is dominated by the deformation in the longitudinal direction of the core.