Composite material missile wing was an important component to provide lift for loitering munition, and the light weight design was the difficulty in structural design of loitering munition. Choosing the composite material missile wing structure of loitering munition as the research object, the finite element model was established. Based on the multi-level optimization function of OptiStruct composite material, and under the condition of the stiffness and strength of composite material coating technology constraints, through the classification optimization of up-and-down skin and spar of missile wing, finally the reduction of the carbon fibre composite material missile wing structure of the high aspect ratio loitering munition was up to 61%.