摘要
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。
The structure design of the unmanned air vehicle(UAV)with multiple rotors is an important process for UAV development.The structure optimization design method is the key for flight safety and performance.A heavy-duty quad-rotor UAV is designed according to the performance requirements that is foldable,light weight,high strength and 10 kg's effective payload.The finite element model of the quad-rotor 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.An UAV static test platform is built,and the structure static loading test is completed.Results show that compared with the initial layout of the 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.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 are verified.
出处
《航空工程进展》
CSCD
2018年第1期99-106,共8页
Advances in Aeronautical Science and Engineering
基金
国家级大学生创新创业训练项目(201510624033)
中国民用航空飞行学院成果转化与创新基金(CJ2013-02)
中国民用航空飞行学院研究生创新项目(X2015-13)
关键词
四旋翼
无人机
结构设计
复合材料
优化
quadrotor
UAV
structure design
composite material
optimization
