Buckling Analysis of Corrugated Plate Fuselage Under Uniform Pressure Loading Condition

Abstract

The optimization of fuselage structures is key focus in domain of aerospace engineering to ensure the weight efficiency, safety and resistance to buckling and deformation under different loading conditions. This study evaluated the static stress and buckling behavior of fuselage section using Finite Element Analysis (FEA). Three distinct fuselage configurations were employed: Skin, Skin with Bulkheads, and Skin with both Bulkheads and Stringers. Titanium alloy Ti-6Al-2Nb was used in all the configurations because of its stability and high strength to weight ratio. FEA using ANSYS was performed to evaluate deformation, stress and buckling performance under uniformly distributed pressure loading. The results show that including stringers significantly improves the structural performance. Design 3, including of bulkheads and stringers, revealed lowest deformation (54.46 mm), lowest von Mises stress (400 MPa) along with highest FoS (2.32) and buckling multiplier (>1). Thus, the study demonstrates that adding appropriate internal reinforcement elements in fuselage structures enhance load bearing capacity and structural stability.