Abstract: The proportion of composite materials used in the aviation field is increasing year by year,and the lightweight design of aircraft structures can be achieved by optimizing the thickness of the composite layer and the size of the structure.Based on the finite element modeling and analysis of a certain type of aircraft wing structure,with the goal of weight reduction,through the control of structural displacement,strain and torsion and other constraint conditions,based on the optimization design function of Nastran,the thickness of the composite layer of structural skins,beams,and ribs and the size of the beam edge strips of the wing structure are optimized. The results show that the optimized wing structure has a significant weight reduction under the premise of ensuring stability.