著者

滝田 好宏 樫谷 賢士

出版者

一般社団法人 日本機械学会

雑誌

Dynamics & Design Conference 2016 (ISSN:24242993)

巻号頁・発行日

pp.431, 2016 (Released:2017-06-19)

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This paper investigates a VTOL UAV with tailless wing configuration. In the previous our work for multi-rotor UAV, a trirotor geometry with four rotors was built and experimented flight in the laboratory. VTOL type UAV enables the flight without take-off and landing spaces. So, there many researches for VTOL type UAVs, but the effective configuration of wing and electric propulsion unit is not discovered. This paper proposes a tailless wing configuration combined with the trirotor geometry for VTOL UAV. The Tailless wing airplane has advantage of low friction force, simple structure and lighter than the normal airplane with same wing area. The disadvantage of tailless wing type is that low stability in pitch and yaw motions. In order to overcome these problems, a stable airfoil with low moment coefficient is used and designed the configuration the wing. The experimental model of tailless wing for VTOL UAV is built and experimented flight in the field. Experimental results show the maneuver of designed tailless wing UAV.