ON THE FINITE ELEMENT ANALYSIS AND EXPERIMENTAL VERIFICATION OF AIRCRAFT FLOOR SANDWICH COMPOSITE PANELS

In this paper, analysis of orthotropic and sandwich structure in different boundary conditions are considered. First, the theoretical background for analysis of orthotropic plates is introduced. Next, a finite element model was developed and used as a numerical tool for analysis of these structures under different load and boundary conditions.The detailed design and analysis of sandwich panel required the input of the elastic and strength properties of the sandwich constituents. For this reason at first an improved testing procedure and its results that provided the basic elastic and strength properties are reported in this paper. The obtained calculation, the deflection and stress for sandwich plate (isotropic face & orthotropic face), considering various boundary conditions such clamped (all edge clamped) and simply supported under local and lateral loads are estimated. Next, finite element method is used to determine the stresses and deflections of panels with various load and boundary conditions. The effect of plate aspect ratio (a/b) on stresses and deflections for simply supported, clamped and bolted condition of a sandwich panel with bolted boundary conditions under lateral load was studied experimentally. The results obtained from FEM, theoretical and experimental investigations are then compared.

Keywords:

FEM , Floor composite Sandwich panel , Experimental test