Analyses of Mechanical Properties of Honeycomb Sandwich Leading Edge of Wing Structures
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.
honeycomb sandwichequivalent elastic constantfailure modefinite element methodcohesive element
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