Critical Bending Stress for Flat Rectangular Plates Supported Along All Edges and Elastically Restrained Against Rotation Along the Unloaded Compression Edge

An analytical solution for elastic buckling analysis of stiffened panel subjected to pure bending

“…The equilibrium method can obtain exact results of critical buckling strength with a high efficiency and has been widely employed for buckling strength calculations of thin plates with different loading and boundary conditions, such as simply supported thin plates under uniform compression [20,21] or under linearly distributed stress [22,23]. The method has also been successfully applied to the buckling analysis of stiffened panels under loading conditions where buckling mainly occurs on the skin, such as compression [24] and eccentric compression along skin [25]. In these cases, the equilibrium equations in the skin of the stiffened panels were used for the buckling calculations and the effect from the stiffener on buckling was considered by adding a special constraint, elastically built-in (an intermediate boundary condition between simply supported and built-in condition), on the joint edge between the skin and stiffener [26].…”

“…The method is much easier to be applied to buckling calculations for structures with complicated geometric conditions, such as stiffened panels, however, the deflection of the buckled structures has to be assumed before the calculations, which raises some uncertainties of the method [29]. Energy method has been applied to calculate the buckling strength of stiffened panels in many studies [30], however, different flexible skin deflection assumptions have been used to consider the interaction between skin and stiffener, such as one half-waves or two halfwaves deflection assumptions [24,25] and deflections defined by trigonometric functions [33,34]. The main limitation of the energy method is that the deflections of the buckled structures are assumed empirically, which is hard to to guarantee the accuracy of the calculated results.…”

Ultimate resistance of longitudinally stiffened curved plates subjected to pure compression

“…The first researches in the field of curved plates were mostly related to aeronautics. Redshaw [19], Marguerre [20] and Stowell [21] all proposed equations for obtaining the elastic critical stress for which they assumed that is equal to the ultimate load of a curved panel. However, several experimental investigations performed in the 1940s on curved panels made of aluminium alloy showed significant differences with theoretical values.…”