微型扑翼飞行器推力特性试验

Experimental investigation of propulsion characteristic of flapping-wing MAV

通过进行微型扑翼飞行器低速风洞试验,研究了扑动翼展弦比、刚度和弯度对其推力特性的影响.制作了展弦比为2,4.5和7以及带弯度与不带弯度的矩形扑动翼,并对三种不同刚度大小的矩形扑动翼进行了结构变形分析;试验风速变化范围从4 m/s到10 m/s,扑动频率从4 Hz到8 Hz.风洞试验结果表明适当的增大扑动翼展弦比或减小扑动翼刚度有助于提高扑翼飞行器的推进效率;而扑动翼翼型弯度的增加不利于推力特性的提高.

In order to investigate the effect of aspect ration and stiffness and camber of flapping-wing on thrust force characteristic, the wind tunnel test of Flapping-wing MAV （Micro air vehicle） was performed in special micro air vehicle wind tunnel of NPU（North- western Polytechnical University）. The rectangular wing which has the aspect ration of 2, 4.5 and 7 and cambered aerofoil and flat aerofoil were fabricated. Structure strength of three different stiffness rectangular flapping-wings was analysed. The velocity （from 4m/s to 10m/s） and flapping frequency （between 4Hz to 8Hz） were applied for test. In this experiment we find it improves thrust efficiency of flapping-wing through increase aspect ration or decrease stiffness of flapping-wing. It is disadvantageous to thrust characteristic through increase camber of airfoil.