Buckling of Aerospace Structures
The modern design of aerospace thin-walled structures is often driven by the stability behaviour. This implies the need to investigate and understand the nonlinear response characteristics under different mechanical and thermal loading conditions. While in the past the buckling load was in most of the cases a limit load, especially for composite structures, nowadays also primary aeronautical structures are proposed to work in the post-buckling field. Design and analysis methodologies are developed, and experimentally validated, for aeronautical components, also taking into account fatigue loading and damage propagation due to large deformation. New aeronautical solutions are also explored for using post-buckling configurations for shape control and morphing applications.