The objective of the current paper is to present a Ritz-type solution for the buckling analysis of cracked-orthogonally stiffened panels. A cracked-orthogonally stiffened panel is defined as a rectangular plate with a crack and that has stiffeners that are parallel to one of its sides. Such structures are typically used as stiffened wing skins and fuselage skins in aerospace engineering. The behavior prediction of a cracked-stiffened panel using the Ritz approach is considered in the paper. In the Ritz-type solution, we use the local trigonometric trial functions to define the displacement function of the crack-stiffened panel, which is discretized into several elements based on the crack location and stiffener location. The interface continuity conditions for cracked thin-walled structures are derived and investigated in detail; the interface conditions are used to condense the global eigenvalue problem by eliminating redundant Ritz coefficients. Examples are presented to illustrate the effectiveness of the current model for buckling analysis. Buckling results from the current model are found to agree well with those obtained using a shell finite element method.
Ritz Approach for Buckling Prediction of Cracked-Stiffened Structures
Journal of Aircraft ; 50 , 3 ; 965-974
2013-03-13
10 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Ritz Approach for Buckling Prediction of Cracked-Stiffened Structures
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