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

Elastic-plastic buckling analysis of stiffened panel subjected to global bending in forming process

“…The buckling behaviour of stiffened panels in the elastic region has been investigated with different loading conditions for different buckling modes, such as under the uniform compression in skin buckling mode [16,17] and the pure bending in stiffener buckling mode [18]. The two main analytical methods for solving the buckling problem are the equilibrium method [19] and the energy method (Ritz method) [20].…”

“…The former can provide a more accurate prediction since the latter is based on the empirical structure deflection assumption [21]. In the equilibrium method, the stiffened panel is simplified to a plate with a rotational constraint, elastically built-in (an intermediate boundary condition between simply supported and built-in) to consider the interaction between the stiffener and the skin [14,18].…”

A Contribution to Analytical Solutions for Buckling Analysis of Axially Compressed Rectangular Stiffened Panels

“…Galé a and Martin [3] presented buckling of stiffened panels in accordance to Eurocode 3 Part 1.5 and developed a general calculation method for critical buckling stress with the help of EBPlate software. Various approaches have been used recently to solve the elastic buckling problems of stiffened panels [4][5][6][7][8][9][10][11][12][13]. In the numerical approach, FEM is widely used for buckling analysis problem irrespective of the boundary conditions and loading type.…”

“…The analytical approach effectively gives exact solutions for buckling problems of stiffened panels. However, despite the fact that several theoretical and experimental studies have been conducted in the past decades to obtain the critical buckling loads of stiffened panels in both uniaxial and biaxial range, some aspects of theories of buckling are still unaddressed largely because of the assumed shape functions and the variation in the number of finite series employed in the analysis [12,14,15].…”

Experimental Validation of Numerical Model of Composite Panel for Aerospace Structural Applications

“…It is understood as high stiffness and minimal weight (Kim et al, 2010). Composite structures provide large weight savings compared to metal structures, while remaining with relatively high stiffness (Zhou et al, 2019). Typical aerospace lightweight structures are sandwich panels (with foam, honeycomb, web or truss core - Arunkumar et al, 2016) or stiffened composite panels (e. g. with blade ribs, T-bar ribs or hat-ribs - Pravallika and Yugender, 2016;Zalewski and Bednarcyk, 2010).…”