ABSTRACT Thin‐walled composite structures are widely used in weight‐critical applications such as aircraft and spacecraft. However, ensuring the stability of such structures under various load cases remains a key challenge in their design and optimization. For omega‐stringer stiffened panels, the local buckling and postbuckling behavior are investigated using closed‐form analytical solutions. The stiffened panel under consideration consists of the skin plate with eccentrically attached stringer feet along the longitudinal sides of the panel, while the remaining part of the omega‐stringer is modeled by corresponding elastically restrained edges. The computational model is based on energy methods and approximates the postbuckling behavior near the bifurcation point using a simplified plate model. To evaluate the new analysis method, a comparison with the finite element analysis is being drawn. Compared to numerical methods, the present model reduces the computational effort, which is particularly advantageous in the design phase.
Yaakoubi‐Mesbah et al. (Wed,) studied this question.