微型扑翼飞行器的升力风洞试验  

Experimental study of flapping-wing MAV in wind tunnel

作　　者：刘岚[1] 方宗德[1] 张西金[1] 

机构地区：[1]西北工业大学机电学院,西安710072

出　　处：《航空动力学报》2007年第8期1315-1319,共5页Journal of Aerospace Power

基　　金：国家自然科学基金(50575183);西北工业大学博士创新基金(M016103);博士点基金(20050699022)

摘　　要：针对微型扑翼飞行器在专门的低雷诺数试验风洞中进行了扑翼的升力风洞试验,测试出了微型扑翼飞行器在正常飞行以及向上爬升状态时的升力特性曲线,并且探讨了扑翼频率、飞行速度以及扑翼的迎角对扑翼飞行升力的影响,在此基础上,还分析了扑翼升力的组成部分以及相互关系.实验结果为微型扑翼飞行器总体、气动的进一步设计提供了依据.The lift wind tunnel tests were conducted for the manufactured flapping-wing MAV（Micro Air Vehicles） in a low Reynolds number wind tunnel of NPU（Northwestern Polytechnical University）. And, the lift characteristic curves of MAV in normal flight and climbing state were measured. Also, the influence of flapping frequency, wind velocity and angle of attack on aerodynamic characteristics was investigated. Based on the wind tunnel test, the composition of flapping lift and their relations were discussed. The test result provide a reference for the design of flapping-wing MAV.

关 键 词：航空、航天推进系统 扑翼 微型飞行器 仿生 风洞试验 升力 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]