柔性扑翼微型飞行器升力和推力机理的风洞试验和飞行试验  

Aerodynamic experimental investigation for mechanism of lift and thrust of flexible flapping-wing MAV

作　　者：昂海松[1] 曾锐[1] 段文博[1] 史志伟[1] 

机构地区：[1]南京航空航天大学微型飞行器研究中心,南京210016

出　　处：《航空动力学报》2007年第11期1838-1845,共8页Journal of Aerospace Power

摘　　要：为探讨柔性扑翼微型飞行器产生升力和推力的机理,在研究考虑柔性大变形扑翼气动力计算方法基础上,利用南京航空航天大学低速风洞进行了不同扑动频率、迎角、速度下微型扑翼升力、推力的变化和动态流场显示等风洞实验,并与计算结果进行了比较分析,为微型扑翼机的设计提供了的参考依据.自行研制的微型柔性结构扑翼机成功地进行了飞行试验.A new flapping-wing model of MAV （Micro Air Vehicle） with flexible structure was developed in order to explore mechanism of lift and thrust generation in flexible flapping-wing MAV. Wind tunnel test demonstrated the downstroke of the flapping-wing by utilizing laser instrument. Variation of the lift and thrust of flexible flapping-wing under conditions of different flap parameters such as flap frequency, angle of attach, flow speed and so on was investigated and compared with computed results. The research provides reference for design of flapping-wing MAV. The flight tests of the Flexible Flapping-wing MAV conducted in Research Center of MAV of NUAA were also successfully completed.

关 键 词：航空 航天推进系统 微型飞行器 扑翼机 柔性扑翼 风洞实验 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]