Design and Flight Test Validation of a Rotor/Fixed-Wing UAV

摘要

Vertical take-off and landing aircraft (VTOL) has been a hot research topic in the aeronautics. This paper discusses the feasibility of a new concept of rotor/fixed-wing which can switch the flying mode during flying. In this design, wings on both sides of the UAV could rotate respectively around the pitch axis to switch the flying mode, so as to achieve the purpose of VTOL or the cruising flight. The paper made an analysis on the aerodynamic characteristics and the mechanical characteristics of this kind of UAV. Based on these study, a physical prototype were made and conducted a flying test, which the recorded date was basically in line with the design goals, the power to weight ratio of the rotor/fixed-wing is significantly greater than the VTOL aircraft which use traditional propeller. It is proved that the analysis on the mechanical characteristics and the aerodynamic characteristics is valid. It illustrates that this aircraft configuration had certain feasibility and paved the way for potential application prospect in the future.