Buckling Analysis of Curve Stiffened Fuselage Panel of Very Light Jet Aircraft

Abstract

Buckling characteristic of curve stiffened fuselage panel of very light jet (VLJ) aircraft which use one of rivet or friction stir welding (FSW) joint on its stringer-frame-skin connections has been investigated by employing finite element methods. The linear and non-linear finite element analyses were used to determine the effects of stringer shapes and pitch on the buckling load of the fuselage panel. The buckling modes of all fuselage panels have also been observed. The material, boundary, and geometric non-linearity were applied on the fuselage panel in the analysis. Degradation of material elastic modulus around Heat Affected Zone (HAZ) due to friction stir welding processes has been taken into account. The results show that the buckling load of curve FSW stiffened fuselage panel slightly smaller than that curve rivet stiffened fuselage panel for all stringer shapes and stringer pitch. Besides, the curve stiffened fuselage panel with a smaller stringer pith has a higher critical buckling load and higher loading capacity. Both curve rivet and curve FSW stiffened fuselage panels with close hat stringer shape have a better loading capacity than with the open hat and the Z-stringer shape.