Design And Research Of Small Coaxial Double Rotor UAV

In recent years,coaxial double-rotor UAVs(unmanned aerial vehicles)have been widely used in military and civilian applications.Compared with conventional drones,coaxial unmanned aerial vehicles have the advantages of strong load capacity,high hovering efficiency,long battery life and compact structure,so they have broad application prospects.However,from the current domestic and international research results,most of the coaxial drones are large in size and weight,and have poor portability.Therefore,it is necessary to research and design a small coaxial double-rotor UAV.This paper studies the overall structure and overall layout of a small coaxial double-rotor UAV,aiming to design a portable coaxial double-rotor UAV.The specific research contents are as follows:(1)The design flow and technical indicators of the small coaxial double-rotor UAV were developed.Through the comparative analysis of the three control schemes,the dual-motor differential control scheme was determined.Furthermore,the overall program of the UAV was designed.It was divided into six subsystems,the functional requirements of each subsystem were clarified,and the overall layout design of the UAV was completed.(2)The rotor load model was established and its maximum total distance and speed were determined.The CFD(computational fluid dynamics)method was used to simulate the load of different rotor pitches,and the optimal spacing of the rotor was determined.The integration method was used to integrate the power required by the rotor and the power required for the whole machine.The structural design of the rotor system and the strength check of the main components were completed.(3)The functional analysis,module division and configuration design of the operating mechanism were carried out,and its kinematics model was established.The dimensional optimization and workspace analysis of the lower operating mechanism were completed.The results show that the designed operating mechanism can meet the requirements of its workspace motion.(4)The structural design of each subsystem of the UAV was completed,and the strength of the important parts was checked.The motion and mechanical properties of the operating mechanism were simulated and analyzed based on ADAMS.The virtual prototype model of the UAV was completed.(5)The prototype of the small coaxial double-rotor UAV prototype was completed.The flight dynamics equation was established based on the prototype,and the dynamic equations were solved to prepare for the design of the flight control system of the subsequent UAV.