具有工程适用性的复合材料机翼结构快速设计

Rapid Design of Composite Wing Structure with Engineering Applicability

为实现复合材料层合板的快速设计,从工程适用性角度出发,提出了面向铺层厚度/铺层顺序的快速设计流程。首先,基于满应变设计方法对复合材料分层厚度进行优化设计,得到各分层的厚度比例。然后,采用相对差商法实现分层厚度的圆整,各分层在圆整之后为单层厚度的整倍数。最后,基于工程材料数据库对铺层顺序进行设计。利用某无人机复合材料机翼对本文提出的设计流程进行了验证,结果表明,机翼减重6.7%,最大变形下降了3.3%,层合板的设计效率明显获得了提升。

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.