Design And Matching Control Of Hybrid Electric Propulsion System For Agile Transport UAV

In recent years,under the national call of "carbon peak,carbon neutral",the field of green energy and electric technology has ushered in a new opportunity for development,and several research institutions have been conducting research in the field of green aviation,which plays a positive role in promoting the development of China’s aviation industry.With the development of UAV technology,the flying machine with fast vertical take-off and landing function has gradually become a research hot spot.In this thesis,following the development status of domestic and foreign oil-electric hybrid electric propulsion UAVs,and drawing on the successful experience of current oil-electric hybrid electric vehicle-related research,a certain type of vertical takeoff and landing fixed-wing UAV is taken as the reference model,and the following research is done on its oil-electric hybrid electric propulsion system configuration,parameter matching and control strategy.(Ⅰ)Design the overall scheme of the oil-electric hybrid electric propulsion system for vertical take-off and landing fixed-wing UAVs,introduce the key components of the system in detail,analyze the factors considered in the selection,and explain the series,parallel and hybrid systems the advantages and disadvantages of the electric propulsion system and its application on the vertical take-off and landing fixed-wing UAV,combined with the structural characteristics and performance requirements of the vertical take-off and landing fixed-wing UAV,the configuration of the electric propulsion system including the extended range and distributed characteristics is designed as a Its dynamic configuration scheme.(Ⅱ)According to the flight characteristics of vertical take-off and landing fixed-wing UAVs,starting from the UAV platform parameters and performance indicators,systematically analyze the performance of UAVs in multi-rotor mode,hovering transition mode and fixed-wing mode power requirements and calculate them.According to the calculation results,combined with the existing key power component devices on the market that meet the expected performance indicators,the DLE170 M aeroengine,TMOTORU15Ⅱ-KV100 rotor motor,U13Ⅱ-KV65 tail rotor motor,and S676-800U-02 generator were finally selected as the motor.For the power components of the propulsion system,G40*13 is selected as the rotor blade,and G32*11 is used as the tail rotor.The matching analysis of tail rotor and motor,rotor and motor shows that the maximum level flight speed is 152.5km/h,which is 1.7% higher than the maximum level flight speed required by the performance index.When the throttle point is 75%-85%,the rotor both the power and speed output by the motor meet the performance requirements,and the matching effect is good.(Ⅲ)In order to further verify the rationality of the hybrid electric propulsion system,simulation analysis and hardware-in-the-loop experiment verification were carried out.Based on the working conditions of fixed flight missions,the hybrid electric propulsion system was modeled and simulated,and the propulsion system simulation model was built by using the existing modules in MATLAB/Simulink.The hybrid electric propulsion system is verified by constant power,fuzzy logic and dynamic programming energy management strategies.The results show that under three different control strategies,the rotor motor and tail rotor motor can operate accurately within the speed range meeting the performance indexes of the UAV,and the control effect of dynamic programming energy management strategy is obviously better than that of constant power and fuzzy logic control strategy.Compared with the first two control strategies,the cumulative fuel consumption is reduced by 5.5% and 6.3% respectively.Based on the simulation results of dynamic programming energy management strategy,a hardware-in-the-loop experiment was carried out to verify the hybrid electric propulsion system based on M2 C development platform.The results show that compared with the simulation results,the accuracy of the battery SOC and motor speed are 98.98% and 99.16% respectively,which further indicates the feasibility of the hybrid electric propulsion system designed in this thesis for VTOL fixed wing UAV.