Plate Buckling Study

Todays, the plates are widely used in various industries such as shipbuilding, aircraft, aerospace, car manufacturing industries, and etc. The plates are under different forces therefor studying on them under different loading and boundary conditions is important. It is possible (maybe) the plate subjected to compressive forces in an engineering structure that it will result buckling. Because of different boundary conditions of plates has been used in the wings of aircraft or in the hulk, the plates are under linearly distributed and uniform compressive in-plane forces, therefore it is important to study the phenomenon of plate buckling. There are many studies about buckling of plates, Abolghasemi and et al. [1] investigated on the buckling

Shiau and et al. [4] studied thermal buckling behavior of composite laminated plates based on classical theory and finite element method. They studied the thermal buckling mode shapes of angle-ply and cross-ply laminates with various boundary condition, fiber angle, aspect ratios, E_1/E_2 ratio. They showed the thermal buckling mode that composite laminated plate depend on aspect ratio, fiber orientation, a_2/a_1 ratio and E_1/E_2 ratio. Javaheri et al. [5] investigated thermal buckling of rectangular FGM plate based on classical theory, under four types of thermal loading including uniform temperature rise, linear temperature change across the thickness, nonlinear temperature change across the thickness and linear temperature change through the length with simply supported boundary conditions. Their results showed by increasing dimension ratio b/a, the critical buckling temperature difference increased as well as by increasing the dimension ratio b/h and the critical buckling temperature difference of FG plate under temperature difference along the length is greater than the FG plate under linear temperature difference across the

They showed when the aspect ratio of plate or the thickness to span ratio increased, the critical buckling temperature difference increased. In recent years, researchers for reinforcement of composites and FG plates used in engineering structures embedded nano tubes, shape memory alloy (SMA), electrorheological fluids, smart materials–piezoelectric materials, etc. Park et al. [7] investigated vibration of thermally post-buckled composite plates embedded with shape memory alloy fibers with simply supported boundary conditions based on the start-order shear deformation plate theory and nonlinear finite element method. The thermal post-buckling deflection was determined based on Newton–Rapson method. By embedding SMA fibers, the thermal large deflection is decreased and the critical temperature is increased. Even though by using SMA fibers, weight of plate was increased but the thermal large deflection was decreased. Lee et al. [8] analyzed buckling and post buckling behavior of laminated composite (carbon/epoxy) shells with embedded shape memory alloy (SMA) wires under axial compressive forces and thermal loading for the cases of two boundary conditions clamped–clamped and simply supported–simply supported boundary