Buckling and post-buckling analysis of composite stiffened panels: A ten-year review (2014-2023)

Composite stiffened panels, known for lightweight, high load-bearing efficiency, and low cost, are commonly used in aerospace structures. These panels are subjected to various loading conditions, including axial compression, shear, or combination, with buckling as a prevalent failure mode. Composite stiffened panels maintain some load-bearing capacity despite buckling, entering a post-buckling state. Researchers commonly employ experimental methods, analytical solutions, and numerical methods to investigate the buckling and postbuckling behavior of composite stiffened panels. Experimental studies highlight failure modes such as skinstiffener debonding, interlaminar damage, and delamination under various conditions. Analytical methods provide computationally efficient solutions during the early design stages. Numerical methods, particularly finite element analysis (FEA), effectively predict critical buckling loads and failure mechanisms, facilitating design optimization and cost savings. This review synthesizes a decade of research into the buckling and post-buckling behaviors of composite stiffened panels, incorporating experimental, analytical, and numerical studies. Insights from these studies highlight the need for advanced predictive models and design methodologies that maximize the weight reduction and efficiency of composite stiffened panels in aerospace applications.