太阳能无人机机翼复合材料主梁铺层优化  

Layer optimization of composite material for wing girder of solar UAV

作　　者：邓忠 支亚非 程家林 杨文 DENG Zhong;ZHI Yafei;CHENG Jialin;YANG Wen(AVIC Chengdu Aircraft Industrial(Group)Co.,Ltd.,Chengdu 610092,China)

机构地区：[1]航空工业成都飞机工业(集团)有限责任公司,成都610092

出　　处：《复合材料科学与工程》2024年第3期108-112,共5页Composites Science and Engineering

摘　　要：太阳能无人机采用超大展弦比机翼,巡航速度低,机翼载荷较小,不能负担过大的结构重量飞行,因此对飞机结构重量的要求严苛。太阳能无人机机翼主梁采用复合材料圆管的形式,机翼主梁占机翼结构的大部分重量,因此需要对机翼复合材料主梁的铺层进行优化设计,以减轻机翼主梁的重量,优化主梁结构传力效果。首先建立了太阳能无人机单边机翼的有限元模型,然后依次对机翼复合材料主梁进行铺层形状优化、铺层厚度优化与铺层顺序优化,优化后机翼主梁重量下降18.68%,最大应力下降21.16%,翼尖变形下降5.9%。Solar UAV adopts super aspect ratio wing,which has low cruise speed,low wing load and can not fly with excessive structural weight.Therefore,it has strict requirements on the weight of aircraft structure.The wing girder of the wing accounts for most of the weight of the wing structure,so it is necessary to optimize the layer of the composite wig girder to reduce the weight of the wing girder and optimize the structural force transmission effect.First,the finite element model of the half wing of the solar UAV is established,and then the shape,the thickness and the order of the wing girder composite is optimized.After optimization,the weight of the wing girder decreases by 18.68%,the maximum stress decreases by 21.16%,and the tip deformation decreases by 5.9%.

关 键 词：太阳能无人机 复合材料 铺层优化 

分 类 号：TB332[一般工业技术—材料科学与工程]