微型扑翼飞行器升力特性研究

Lift characteristic of the flapping wing micro air vehicle

为了对微型扑翼飞行器升力机理进行探索性研究,本文利用西北工业大学微型飞行器专用风洞进行了扑动翼频率、风速、迎角、扑动翼弯度对其升力特性影响的研究。并且利用示波器对扑动翼扑动相位角和产生升力大小之间的关系进行了研究。试验结果表明升力特性的研究为微型扑翼飞行器总体设计和气动布局设计提供了一定的工程指导。

In order to exploringly investigate lift mechanism of flapping-wing MAV（Micro Air Vehicle）, the lift test of flapping-wing MAV is performed in special micro air vehicle wind tunnel of NPU（Northwestern Polytechnical University）. The influenees of flapping frequency, wind velocity, angle of attack and camber of flapping-wing on lift characteristic are investigated. The relation between phase-angle of flapping andthe magnitude of lift force is investigated. The result of wind tunnel test provides guideline in aircraft design and aerodynamic layout design of flapping-wing MAV.