Flight Testing Small, Electric Powered Unmanned Aerial Vehicles
Flight Testing Small, Electric Powered Unmanned Aerial Vehicles
复制标题
小型电动无人机的飞行测试
DOI：
10.2514/6.2005-7654
复制
发表时间：
2005
影响因子：
10.4
通讯作者：
J. Ostler
中科院分区：
文献类型：
--
作者：
J. Ostler
提出了小型电动变距螺旋桨无人机阻力极线的飞行试验方法。风洞试验用于表征螺旋桨发动机效率。阻力极线是利用在不同空速下进行的∞ight试验的数据建立的。所提出的方法实现了一个小型无人机。该飞机的阻力极线CDo等于0.021，K1等于0.229，K2等于-0.056。
Flight testing methods are proposed to flnd the drag polar for small UAVs powered by electric motors with flxed-pitch propellers. Wind tunnel testing was used to characterize the propeller-motor e‐ciency. The drag polar was constructed using data from ∞ight tests at various airspeeds. The proposed methods are implemented for a small UAV. A drag polar was found for this aircraft with CDo equal to 0.021, K1 equal to 0.229, and K2 equal to -0.056.