玻璃钢/复合材料Issue(4)：17-23,7.
基于有限元的四旋翼无人机碳纤维结构优化设计与固有模态分析
THE OPTIMIZATION DESIGN OF QUADROTOR UAV CARBON FIBER STRUCTURE AND NATURAL VIBRATION ANALYSIS BASED ON FINITE ELEMENT METHOD
摘要
Abstract
According to the performance requirements, a full carbon fiber structural consumer-grade quadrotor UAV is designed,which has the features of light weight, high strength, long navigation time and simple configuration.The finite element model of quadrotor UAV structure is established, and the structure stress state of the UAV under the rated load is analyzed.The structure strength is checked based on the maximum stress strength criterion.The stability of the initial UAV structure is analyzed, and the critical buckling load and buckling modes are calculated.Based on the minimum weight requirement, the carbon fiber laminates optimization design of the initial structure is carried out.The natural vibration analysis of the optimized structure is conducted, and the first four natural frequencies and vibration modes are given.Under condition of 2 g load factor, the structure ultimate load is 2.57 times of the maximum service load, and the buckling critical load is 2.09 times of the maximum service load.The design goals and requirements are met.The weight of optimized structure is decreased by 21％, and reduced to 108.6 g.Payload is about three times of the structure weight.关键词
四旋翼/无人机/有限元/碳纤维/结构优化Key words
four rotor/UAV/finite element/carbon fiber/structure optimization/vibration引用本文复制引用
刘峰,高鸿渐,喻辉,代海亮..基于有限元的四旋翼无人机碳纤维结构优化设计与固有模态分析[J].玻璃钢/复合材料,2017,(4):17-23,7.基金项目
中国民用航空飞行学院成果转化与创新基金项目(CJ2013-02) （CJ2013-02）
国家级大学生创新创业训练项目(201510624033) （201510624033）
中国民用航空飞行学院研究生创新项目(X2016-34) （X2016-34）
