主管单位：中华人民共和国工业和信息化部
主办单位：西北工业大学 中国航空学会
地 址：西北工业大学友谊校区航空楼
主办单位：西北工业大学 中国航空学会
地 址：西北工业大学友谊校区航空楼
中国民用航空飞行学院,中国民用航空局第二研究所,中国民用航空飞行学院,中国民用航空飞行学院,中国民用航空飞行学院
TB121
Civil Aviation Flight University of China,Second institute of civil aviation administration of China,Civil Aviation Flight University of China,Civil Aviation Flight University of China,Civil Aviation Flight University of China
多旋翼无人机结构设计是无人机研制的重要环节,结构优化设计方法是保证无人机安全飞行、提高无人机性能的关键。根据重载四旋翼无人机性能要求,设计一款最大有效载荷10kg、可折叠、质量轻、强度高的四旋翼无人机。建立无人机结构有限元模型,基于实际工况对机臂及中心板进行静力及屈曲分析;对机臂及中心板的铺层方案进行优化,校核结构强度、刚度和稳定性;并搭建无人机静力测试平台,完成重载四旋翼无人机结构静力加载试验。结果表明:相对结构初始铺层方案,机臂减重43%,中心板减重35%,全机结构累计减重560g;试验测点的应变值与分析值相对误差小于15%,验证了无人机有限元模型和优化设计方案的可靠性。
A heavy-duty quadrotor UAV which has the features of foldable, light weight, high strength is designed according to the performance requirements. The maximum payload of this UAV is 10kg. The finite element model of the quadrotor structure is established. Static and buckling analysis of the UAV arm and central plate are carried out based on the actual loading cases. The layer structures of the arm and central plate are optimized. The strength, stiffness and stability of the UAV are verified. Compared with the initial layer structures, the weight of the arms drops by 43%, and the weight of the central plate drops by 35%. The weight of the UAV structure drops by 560 grams. The lowest weight requirement is achieved. An UAV static test platform is built, and the structure static loading test is completed. The strain relative error between the test value and the analysis value is less than 15%. The reliability of the UAV finite element model and the optimized layer structures is verified.
刘峰,喻辉,高鸿渐,代海亮,马佳.重载四旋翼无人机结构优化设计与强度计算[J].航空工程进展,2018,9(1):99-106
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