Probabilistic Approach to Buckling Analysis of Thin Panels Subject to Combined Loads

 

Vladimir Zeljković

Katarina Maksimović

Jezdimir Knežević

 

This paper gives the procedure for the reliability calculation of mechanical components and structures. The stability (buckling) of a tin panel subjected to in-plane combined (normal and shearing) loads is considered in particular. The attention is focused on the buckling analysis of the typical thin-walled aircraft structure such as the skin of wings or fuselage. In this analysis the variables are treated as stochastic: loads, thickness and width of the panel. The numerical example illustrates the procedure. The probability of buckling is calculated for the wing skin of a light trainer aircraft. The effect of the panel thickness (t) and the load factor (j) on the buckling probability is shown. The dimensional tolerance levels affect the critical stress calculation as well as the buckling probability. The variation of the parameters (especially the thickness effect on the buckling) is facilitated by a software program for reliability calculation.

Key words: structure load, panel, panel structure, skin, fuselage, aircraaft wing, structure stability, stability analysis, stochastic variable, probabilistic analysis.