Study Of The Ultimateload Of The Composite Sandwich Plate

As lightening of aircraft structures is aspired and compositestructures are more used in aircraft, because composite sandwichstructures have light weight and high ratios of flexure stiffness to weightas well as strength to weight, composite sandwich structures have beenwidely used in aeronautics field and have been used in substructure andprimary structure.To further improve composite sandwich structures designperformance, security and economical efficiency, the ultimate bearingcapacity of composite sandwich structures need to be fully researched. Inthis paper, analysis of the ultimate bearing capacity of foam-coredcomposite sandwich structures at in-plane load and the ultimate bearingcapacity character have been studied.Firstly, there give mechanical analysis, section property andequilibrium equation of sandwich structures. Buckling of the sandwichstructure give an expression of the buckling coefficient K of the simplesupported isotropic sandwich structure. Analysis of failure modes ofcomposite sandwich is studied.The analysis method of the ultimate bearing capacity based on nonlinear theory is studied. This method considers geometric nonlinearityand introduce strength failure criterion of material, stability problem isassociated with strength problem. Adopted by the displacement andnonlinear finite element calculation, it gives load-displacement curve andultimate load.Analysis of the ultimate bearing capacity of the typical foam-coredcomposite sandwich plate at in-plane load is studied. It researches theinfluence of the sandwich structure thickness and varieties of foam on theultimate bearing capacity and give comparative analysis of sandwichplate and sandwich plate.Finally, the analysis method of the ultimate bearing capacity is usedin foam-cored composite sandwich skin structure of the typical box of anaircraft.