微小型旋翼无人机总体设计与实现  

Design and Implement of a Micro Rotary-wing Aerial Vehicle

作　　者：何宇[1] 刘海军[1] 刘博[1] 

机构地区：[1]中国航天科工集团二院二部,北京100854

出　　处：《战术导弹技术》2012年第4期9-15,共7页Tactical Missile Technology

摘　　要：主要讨论了一种微小型旋翼无人机的设计、制造与试飞验证。在研究涵道风扇式与"单旋翼+气动面"布局的微小型旋翼无人机特点的基础上,提出了微小型旋翼无人机总体设计方案。利用计算流体力学软件Fluent完成了该微型无人机气动面的设计;利用微机电系统惯性测量组件以及地面控制系统完成了该无人机的控制系统设计。微小型旋翼无人机完成了系绳试飞和自由试飞。证明了该微型无人机具有自主悬停能力,并且验证了设计方案的正确性和合理性。The design, fabrication and evaluation of a micro rotary-wing aerial vehicle are reported. Based on the research on the single-rotor and aerodynamic vane structure, the overall design of the micro rotary-wing aerial vehicle is proposed. The aerodynamic surface is designed based on CFD analysis; the control system is accomplished with MEMS IMU and ground control system. The tethered flight test and the free flight test proved that the micro rotary-wing aerial vehicle has the ability to autonomously hover, and validate the design.

关 键 词：微型旋翼无人机 CFD 飞行试验 

分 类 号：V221[航空宇航科学与技术—飞行器设计]