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Corresponding Author

Abdel-Samad, Abdou

Subject Area

Mechanical Power Engineering

Article Type

Original Study

Abstract

An advantage of composite materials over conventional ones is the possibility of tailoring their properties to the specific requirements of a given application. The tailoring is mostly achieved by maximizing the mechanical properties as a result of selecting the fiber angles of the layers optimally so A numerical study was carried out, First to determine the effects of symmetric and anti-symmetric laminate configuration and various boundary conditions on the buckling behavior of E/glass-epoxy composite plates using two different initial laminate configurations ([90/45/-45/0]as and [90/45/-45/0]) as initial fiber orientation, Second to optimize the fiber orientation (ply angles) for maximizing the critical buckling load of B/glass-epoxy composite plates, Finally the initial buckling values and initial fiber angles were compared with optimum buckling values and Optimum fiber angles for the same boundary condition. The four boundary conditions in this study are (clamped-clamped [CC], clamped-pinned (CP], pinned-pinned [PP] and Clamped-Free (CF]). The results mirrored that the buckling load have great effect by changing the boundary conditions. The maximum critical buckling load value is for clamped clamped boundary condition and the minimum value is for clamped free boundary condition. The buckling loads and fiber orientations of the laminated composite were calculated and optimized by ANSYS finite-element computer code.

Keywords

Laminated composites; buckling strength; Finite Element Analysis; Stacking sequence optimization; fiber orientation optimization

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