Composite lay-up and three dimensional finite element model of composite stiffened panel are created using the “laminate modeler” module based on manufacture process. A method for nodes merging of solid element and shell element is introduced. Finite element meshes of the stiffened panel are created with different relative node interval. The convergence of the finite element analysis is verified according to the criterion of maximum Von Mises stress of the panel. The value of 1/72 as a reasonable relative node interval of stiffened panel modeling is obtained. Stress analysis shows that the initial damage of composite stiffened panel under concentrated load occurs in the No. eight layer. The damage mode is matrix crack in the direction of second material axis. The ultimate load of initial damage for the stiffened panel is 75 N. Stress concentration area is small and it’ s distributed in the domain around the loading point. The efficiency of composite stiffened panel under concentrated load is fairly low.