無尾翼機にチルトロータを持つVTOL型UAVの水平飛行における抗力低減

抄録

This paper is a study on Tailless Quad Tilt Rotor VTOL UAV which is designed and demonstrated by our team. For the practical use of proposed VTOL system, it is necessary to achieve a long distance and a long time in level flight. This paper discusses the induced drag at wing tip of tailless wing which is a main wing of UAV. For the conventional aircrafts winglets are used to reduce the induced drag. By our experimental flight of small tailless wing with winglets, the flight stability was found that easy to lose in gust wind. So this paper is selected to optimize the shape of wing tip for reducing induced drag of tailless wing. Experimental results in wind tunnel and calculated results using CFD software are shown by incorporating several types of wing tips.