Wind Tunnel Tests of A Ducted Fan Micro Aerial Vehicle
As part of research and development of an electric ducted fan micro aerial vehicle (EDF -MAV ), we carried out wind-tunnel tests by using a full -scale powered model to obtain data on the aerodynamic characteristics of the EDF -MAV. The potential flight phases of this vertical takeoff and landing (VTOL) vehicle were simulated under a wide range of flight conditions; for this purpose, simulations were performed using various propeller advance ratios and angles of attack. The characteristics of the pitch - up moment of the duct under crosswind conditions were determined in this study, as knowledge of these characteristics is critical for vehicle attitude control. The control moment generated by the vanes was also measured using three different vane configurations to analyze the trim capability of the vehicle for various attitudes. The data obtained in these tests were used to develop methods for improving the vehicle design. Thus, numerical simulations could be carried out for analyzing the dynamics of the vehicle and for designing a suitable control system.
ducted fans micro - aerial vehicle wind tunnel test
Takashi Shibui Takeshi Tsuchiya Shinji Suzuki Daisuke Kubo
Department of Aeronautics and Astronautics, The University of Tokyo,Tokyo,Japan Department of Aeronautics and Astronautics, The University of Tokyo, Tokyo, Japan Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency, Tokyo, Japan
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
145-148
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）