Design And Simulation Of Coaxial Double Rotor Tethered UAV Mechanism

As a new type of,aerostat,the mooring drone is usually composed of a rotorless drone,a tethered cable,and a ground take-off and landing platform.It can be grounded for long periods of time and can be hovered according to different equipments carried by the fuselage.Implement different functions.In this paper,the main body of the mooring drone,the coaxial double-rotor UAV,is studied.The basic theoretical calculation method of the aerodynamic characteristics of the coaxial double-rotor is studied.The numerical simulation of the rotor system is carried out by CFD,and the results satisfying the design requirements are obtained.And carry out the development of physical prototypes.The specific research contents are as fo lows:The overall structure of the coaxial double-rotor UAV is designed.The overall layout of the UAV is determined,and the takeoff weight of the UAV is systematically estimated.The aerodynamic characteristics of the upper and lower rotors of the UAV under the coaxial double-rotor structure are analyzed by the leaf-momentum theory,which lays a theoretical foundation for the subsequent numerical simulation.The aerodynamic shape design of the lower wing of the mooring drone is determined,the main parameters of the rotor are determined,and the attitude control mechanism of the drone is studied.Finally,the two-dimensional and three-dimensional digital modeling of the rotor and the whole structure of the drone are carried out.According to the established drone model,ICEM is used to mesh the rotation domain and the outer watershed of the upper and lower rotors of the UAV.The ANSYS Fluent software is combined with the Navier-Stokes master equation,the density-based coupling implicit algorithm and the Standard.The k-epsilon turbulence model establishes a numerical calculation model suitable for the coaxial double-rotor structure.The model of different rotational speeds and different rotor pitches is analyzed several times,and finally the experimental data that meets the design requirements and has good effects is obtained.According to the established three-dimensional digital model and CFD numerical simulation results,the physical prototype was developed and the flight test was carried out to verify the feasibility and correctness of the design.