A parametric study of the effects of instability for thin composite structures by the finite element method: Buckling of FRP plates [Étude paramétrique des effets d'instabilités des structures minces composites par la méthode des éléments finis : Flambage des plaques FRP]

The analysis of buckling behavior for orthotropic laminated composite plates is important factors in safe and reliable design of the aircraft components and civil structures. the aim of the current research is to investigate the critical buckling load (nx,cr) of reinforced (frp) plates. the loads depends on many parameters like as geometric aspect ratio (a / b),laminate thickness (t),orientation of fiber layers boundary conditions. effects of these variables on critical buckling load of the laminate were analyzed using finite element software (ansys 14.5).it was found that for the analysis of laminated plates simply supported in all edges (s-s-s-s),the optimum orientation of the fiber layers is: [90/45/-45] s degrees for all thicknesses with aspect ratio of 1.0 and 2.0. however,the critical buckling loads increase with increasing aspect ratio and of course with increasing plate thickness.