机翼前缘蜂窝夹层结构力学性能分析  

Analyses of Mechanical Properties of Honeycomb Sandwich Leading Edge of Wing Structures

作　　者：赵慧 吴晓强 ZHAO Hui;WU Xiaoqiang(School of Aircraft Engineering,Xi’an Aeronautical University,Xi’an 710077,China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西安航空学院飞行器学院,陕西西安710077 [2]西北工业大学航空学院,陕西西安710072

出　　处：《郑州航空工业管理学院学报》2024年第5期13-19,共7页Journal of Zhengzhou University of Aeronautics

摘　　要：研究机翼前缘蜂窝夹层结构在上翼面均布气动载荷作用下的力学性能。首先给出蜂窝夹层结构芯层等效弹性参数,用修正后的Gibson模型,将离散蜂窝芯结构按照力学等效的原则转化为均质的三维正交各向异性材料;然后用内聚力单元对蜂窝芯和面板之间的胶接界面进行建模,用壳单元对碳纤维增强复合材料面板进行建模;最后,利用有限元方法,对整个蜂窝夹层结构进行力学性能分析,显示了蜂窝芯和复合材料面板之间的剥离过程,对蜂窝芯和面板剥离破坏模式以及复合材料面板损伤破坏模式进行了分析。The mechanical properties of the whole honeycomb sandwich structure under the uniform aerodynamic loads of leading edge of the wing are studied in this paper.Firstly,the equivalent elastic parameters of the core layer of honeycomb sandwich structure are given,and the discrete honeycomb core in the structure is transformed into a homogeneous three-dimensional orthogonal anisotropic material according to the principle of mechanical equivalence by using the modified Gibson model.Then The bonding interfaces between the honeycomb core and the panels are modeled by the cohesive elements,and the carbon fiber reinforced composite panels are modeled with shell elements.Finally,the mechanical properties of the whole honeycomb sandwich structure are analyzed by using finite element method,showing the delamination process between the honeycomb core and the composite panel and the failure modes of the leading edge structure of the wing are obtained.

关 键 词：蜂窝夹层结构 等效弹性常数 破坏模式 有限单元法 内聚力单元 

分 类 号：V214.6[航空宇航科学与技术—航空宇航推进理论与工程]