Compressive experiments on aero composite stiffened panel were conducted to study the carrying capacity

failure modes and post-buckling failure characterization. The results showed that the composite stiffened panel had a high post-buckling carrying capacity. The failure load was almost 2.2 times of the buckling load. The skin bay initiated buckling first. However

the stiffeners had no buckling before failure

which worked as ‘skin buckling separated’. According to the theoretical analysis

theoretical buckling and failure load had an error less than 8% compared with the experimental results. Additionally

the variation of the out-of-plane displacement on skin center and distribution of the axial compressive load were determined in the post-buckling process.