Composite stiffened panel structure is widely used in modern aircraft

which is prone to buckling under working conditions.A large number of tests show that the aircraft composite stiffened thin-wall structure has considerable post-buckling bearing capacity.The design scheme of the stiffened fuselage curved panel with inner cladding and without inner cladding was proposed.The buckling load

bearing capacity and failure mode of the two kinds of curved panels with inner cladding and without inner cladding were calculated by using Abaqus under axial compressive load

pure shear load and compressive shear combined load.In the model

the Tsai-Wu criterion was used as the failure criterion of composite materials

and the damage evolution was realized by the subroutine Usdfld.It is found that the inner cladding of the hat stringer can significantly improve the post-buckling capacity of the structure and prolong the post-buckling process.