Abstract: The large-scale application of composite materials is the main means of weight reduction for aircraft stiffened panel structures, but due to overly conservative design criteria, the weight reduction effect of the structure is not ideal. Thin-walled stiffened panel structures usually have a long post-buckling bearing history, but due to the lack of effective analysis methods for post-buckling design and evaluation, currently, aircraft composite stiffened panels almost do not allow the skin to buckle below the limited load, which cannot fully utilize the weight reduction characteristics of composite materials. This article reviewed the development process of stability design for composite stiffened panels and elaborates on the necessity of conducting post-buckling design analysis, and provided a detailed review of the research progress on the buckling and post-buckling performance analysis and design methods of stiffened panel structures, focusing on two aspects: engineering analysis technology and numerical analysis technology; Explored the main factors affecting the buckling and post-buckling performance of composite stiffened panels, and discussed the effects of buckling fatigue, damage/defects, and humid thermal environment on structural performance; Finally, the overall status of post-buckling design and analysis technology for composite stiffened panels was summarized, and future technological development trends were discussed.