Buckling Analysis of Carbon Epoxy Trailing Edge Wing Rib

For Aerodynamic reasons, the chord wise of wing contour must be maintained without appreciable distortion. To hold the skin's stringer wing surface to required contour shape, and also to limit the length of the stringers to an efficient column compressive length, internal supporting units are required. These supporting units are referred to as wing ribs. In the current report, a complete stress analysis subjected to different kinds of loading for a wing rib is introduced. The shape of the wing is maintained by wing rib, and it also supports the bending and compressive loads which act on the wing. The objective was to reduce the weight of the rib and increase the critical buckling strength. Linear static analysis and buckling analysis are performed on the idealized configuration of a plate rib using FEM packages. When the detail design of a wing rib under different loading conditions is subjected to buckling, it is found to be safe. Finally, we concluded that initially the design is of 4.592 Kg & optimize up to 2.964 Kg, so that weight is reduce by 1.628 Kg