Abstract: Composite stiffened panels are widely used in aircraft load-bearing components in the aerospace field due to their excellent lightweight, high strength and high stiffness properties. With the continuous improvement of material performance requirements, it is particularly important to have a deep understanding of the buckling and post-buckling behavior of such structures. This article reviews the research progress on buckling and post-buckling properties of composite stiffened panels, and systematically summarizes theoretical approach, finite element simulation technology and experimental research methods. Studies have shown that the geometric parameters (such as height and spacing of stiffeners) and lay-up sequence of stiffened panels significantly affect the buckling performance. At the same time, considering material nonlinearity and geometric nonlinearity is crucial to accurately predict post-buckling behavior. In addition, this article explores the key technical difficulties in predicting buckling and post-buckling failure modes and loads of composite stiffened panels. By analyzing the limitations of existing researches, this article points out possible future research directions, providing a theoretical basis and practical guidance for buckling and post-buckling research on composite stiffened panels and their engineering applications.