扑翼微型飞行器风洞动态试验  

Wind Tunnel Dynamic Experiments of Flapping-wing MAV

作　　者：朱保利[1] 李强[1] 邹俊伟[1] 陈光盛[1] 

机构地区：[1]南昌航空大学,江西南昌330063

出　　处：《南昌航空大学学报（自然科学版）》2011年第1期18-21,共4页Journal of Nanchang Hangkong University(Natural Sciences)

基　　金：航空科学基金项目(2009ZA56001)

摘　　要：文章在低速风洞中进行了多自由度扑翼微型飞行器的吹风试验,实测了扑翼机的升力、阻力随扑动频率、迎角和来流速度等参数的不同而导致的变化情况,测量的扑动参数对扑翼微型飞行器的气动力特性均有较大的影响。In order to investigate the MAV＇s aerodynamic characteristics,using multi-DOF flapping-wing MAV,the load measurement experiment was done in low-speed wind tunnel.The lift and drag were measured with different flapping frequency,attack angle and free-stream velocity.The influence of the flapping parameters on the MAV＇s aerodynamic characteristics was reported.The results could be helpful for the design of multi-DOF flapping-wing MAV.

关 键 词：微型飞行器 扑翼 扑动参数 风洞试验 

分 类 号：V211.753[航空宇航科学与技术—航空宇航推进理论与工程]