尾座式电动飞机复合材料机翼结构优化设计  

Structural optimization for composite wings of tail-sitter electric aircraft

作　　者：麻震宇[1] 张祎桀 张琪 邓小龙 于乃辉 MA Zhenyu;ZHANG Yijie;ZHANG Qi;DENG Xiaoong;YU Naihui(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;Department of Mechanical Engineering,PLA Army Academy of Artillery and Air Defense,Hefei 230031,China)

机构地区：[1]国防科技大学空天科学学院,湖南长沙410073 [2]陆军炮兵防空兵学院机械工程系,安徽合肥230031

出　　处：《国防科技大学学报》2023年第6期20-31,共12页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(51605484);国家重大专项支持项目资助项目(GFZX040201)。

摘　　要：以复杂地形地区物资快速投送平台设计为背景,开展尾座式电动飞机复合材料机翼设计研究。对机翼结构载荷进行分析,对机翼结构构件布置和铺层进行设计,形成复合材料机翼结构设计方案。建立复合材料机翼结构有限元模型,开展典型工况条件下的静力分析,得到机翼结构变形、应力和Tsai-Wu失效因子分布。采用分步优化策略,以机翼结构铺层厚度和铺层角度为设计变量,开展机翼结构质量优化计算,优化结果表明,优化后的机翼结构在满足强度和刚度要求下质量减轻约47.77%,可为尾座式电动飞机结构设计提供重要参考。According to the requirements of material delivery platform in the complex terrain area,the research on the structural design of the composite wing of the tail-sitter electric aircraft was carried out.Based on the load analysis,the structural configuration and lay out designs were studied,and the structural design scheme of the composite wing was proposed.The finite element model of the composite wing was developed and the static strength analyses under different operating conditions were completed.The deformation,structural stress,and Tsai-Wu failure factor distribution of the wing structure were obtained.The structural optimal analysis of the composite wing was performed on the basis of the stepwise optimization strategy with the layer thicknesses and angles as design variables.The optimal results show that the structural mass is reduced by 47.77% under the constraints of structural stiffness and strength,which can provide the important reference for the design and development of the tail-sitter electric aircraft structure.

关 键 词：尾座式电动飞机 复合材料机翼 有限元分析 结构优化设计 

分 类 号：V22[航空宇航科学与技术—飞行器设计]