Abstract: A post-buckling failure evaluation method of integrated composite stiffened panels is required for improving the structure design of composite stiffened panels effectively in the aircraft structure design under uniaxial compression. Finite element models were built using commercial finite element software ABAQUS for the study of the failure evaluation method of integrated composite stiffened panels under uniaxial compression at the post-buckling stage, which was also called "global-local" analysis technique. The study of post-buckling failure for a single-stiffener panel shows that "global-local" analysis technique can provide the displacement and load at the initial point of debonding, and the failure load can also be predicted accurately. The "global-local" analysis technique therefore is demonstrated to be an efficient method for rapid evaluation on post-buckling failure of stiffened panels under uniaxial compression, and is significant for improving efficiency of structure design and lightening aircraft's structure weight.