复合材料弹翼是为巡飞弹提供升力的重要结构部件,其减重设计是巡飞弹结构设计中的难点。文中以巡飞弹复合材料弹翼结构为研究对象建立有限元模型,并基于OptiStruct复合材料多级优化的功能,在刚度、强度及复合材料铺层工艺等约束边界条件下,通过对弹翼上下蒙皮和翼梁分级优化,最终使得大展弦比巡飞弹碳纤维复合材料弹翼结构减重达61%。

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%.