Compression Buckling Analysis of Vertical Tail Stiffened Panels

Thin structural members are susceptible to buckling under compression loading. Aircraft skin is always thin irrespective of the size of the aircraft. Therefore, when the skin undergoes compression, it is likely to buckle. Vertical tail of the aircraft experiences bending, whenever the rudder is deflected to achieve the yawing motion of the aircraft. Side load will cause the bending of the vertical tail, which introduces tension and compression stress field in the two side skins respectively. This project includes the linear static analysis of the vertical tail box structure and buckling analysis of the stiffened panels undergoing compression. A linear static buckling analysis of the vertical tail box structure will be carried out to identify the most critical panel. After that the critical panel is taken for buckling analysis.