Abstract: In order to realize the rapid design of composite laminates,from the perspective of engineering applicability,a rapid design process for ply thickness/ply sequence is proposed. First,based on the full strain design method,the layer thickness of the composite material is optimized,and the thickness ratio of each layer is obtained. Then,the relative difference quotient method is used to achieve the rounding of the layer thickness,and each layer is an integral multiple of the single layer thickness after rounding. Finally,the ply sequence is designed based on the engineering material database.The design process is verified by using the composite wing of a certain type of UAV. The results show that the weight of the wing is reduced by 6. 7%,and the maximum deformation is reduced by 3. 3%. The design efficiency of the laminate is significantly improved.