Research On Variable Collective-Pitch And Rotor RPM Quadrotor UAV Design

This paper presents a new method of designing a quadrotor unmanned aerial vehicle(UAV), which uses the traditional helicopter rotor to improve the efficiency of the rotor, and improve the operating efficiency by variable-pitch and reduce the required power by variable-rotate speed so that the performance of quadrotor UAV will be improved significantly.Firstly, in this paper the domestic and foreign research status and development trend of multi-rotor UAV are introduced and the problem of the quadrotor UAV is presented. Secondly, according to the technology of variable-pitch and variable-rotate speed, the flight performance of quadrotor is calculated,which is based on the theory of blade element theory, momentum theory and engineering empirical formula. Thirdly, the three-dimensional model of the aircraft is established, and an aircraft for flight test is made and the layout and installation method of the mechanical structure system are described in detail. Then through the establishment of quadrotor flight dynamics model, the influence in control-stability is analyzed when the quadrotor is controlled by variable-pitch and variable-rotate speed. Finally, the flight test is carried out. The test results show the feasibility of the proposed method and verify the correctness of the method.Through theoretical calculation and experimental verification, it is proved that the overall configuration of the quadrotor UAV is feasible, and has certain development potential with better flight performance.