变旋翼垂直起降无人机设计与实验  

Design and experiment of variable rotor vertical take-off and landing UAV

作　　者：朱睿 温潍齐 何星宇 赵晨鸿 张焕彬 刘志荣 ZHU Rui;WEN Weiqi;HE Xingyu;ZHAO Chenhong;ZHANG Huanbin;LIU Zhirong(School of Aerospace Engineering,Xiamen University,Xiamen 361101,China;Information Engineering School,Xizang Minzu University,Xianyang 712082,China)

机构地区：[1]厦门大学航空航天学院,福建厦门361101 [2]西藏民族大学信息工程学院,陕西咸阳712082

出　　处：《实验技术与管理》2023年第3期145-151,共7页Experimental Technology and Management

基　　金：福建省自然科学基金面上项目(2022J01058);厦门市自然科学基金面上项目(3502Z20227179);气动噪声控制重点实验室研究基金项目(2201ANCL20220105);西藏民族大学校内科研项目(23MDY03)。

摘　　要：复合式垂直起降(VTOL)无人机结合多种飞行模式,适应多元化的飞行需求。该文提出一种变旋翼电动VTOL无人机结构设计方案,通过结合固定翼和旋翼机的飞行优势,改变旋翼的转向结构及其相对气流的工作方向,从而切换不同气动方式,达到增强机动性、提升续航性的设计目的。在选型和计算校核后,设计样机并搭建实验平台测试其升转速力特性,得出25°~30°为最优攻角,并验证了新系统最大可达传统旋翼1.8倍的升力。以CFD进行验证计算与实验间的偏差控制在7%,结果显示设计可行。Compound vertical take-off and landing(VTOL)UAV combines a variety of flight modes to adapt to more diversified flight requirements.This paper proposes a structural design scheme of variable-rotor electric VTOL UAV.By combining the flight advantages of fixed-wing and rotorcraft,the steering structure of the rotor and its working direction relative to the airflow are changed,so as to switch different aerodynamic modes to achieve the design purpose of enhancing maneuverability and improving endurance.After selection,calculation and verification,the prototype is designed and an experimental platform is built to test the force characteristics of the rotating speed.It is concluded that 25°~30°is the optimal angle of attack,and it is verified that the variable rotor system could reach the maximum lift force of 1.8 times that of the traditional rotor.The deviation between CFD calculation and experiment is controlled at 7%,and the results show that the design is feasible.

关 键 词：垂直起降 无人机设计 样机实验 变旋翼结构 气动特性 

分 类 号：V275[航空宇航科学与技术—飞行器设计]