Abstract
This paper investigates a hybrid type UAV of which configuration is fixed wing with multi-rotor enabled vertical take-off and landing. 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. We propose 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. In the previous research a tailless wing is built with a hole for the front part of trirotor mechanism. Then the experimental tailless wing model carried out stable flight in the test field. Wind tunnel is used to measure the tailless wing with/without a hole. This paper discusses the aerodynamics of proposed fixed wing platform of VTOL UAV.
