- 著者
- 大瀬戸 篤司 近野 敦 増子 弘二 小泉 卓也 内山 勝
- 出版者
- 一般社団法人 日本機械学会
- 雑誌
- ロボティクス・メカトロニクス講演会講演概要集 2012 (ISSN:24243124)
- 巻号頁・発行日
- pp._2A1-H10_1-_2A1-H10_4, 2012-05-27 (Released:2017-06-19)
- 被引用文献数
- 1 1
Quad rotor helicopters has simple mechanism and high stability. However, it is not easy for a quad rotor helicopter to fly long time and long distance, because most of the thrust is consumed to lift the body, and hence horizontal component of the thrust is small. In this paper, we present the experimental results of a quad rotor tail-sitter UAV (Unmanned Aerial Vehicle) which is composed of a quad rotors and fixed wing. Developed UAV can hover like a quad rotor helicopter, and can fly long distance like a fixed wing airplane. We designe attitude and altitude control system of the UAV for hovering. In order to verify the designed control systems, we conducted hovering control flight experiment. Additionally, we identified both the impact of propeller slipstream on yaw control and the solutions.