Determination And Optimization Of The Wind Force Influence Function Of Single Rotor UAV

Due to the low cost,light weight,flexible handling,high maneuverability,ability of vertical taking-off and landing,the single rotor unmanned aerial vehicle has a broad application prospect.However,the complex low-altitude aerodynamic environment makes the actual flight of UAV subject to a large degree of restrictions,leading to the single rotor UAV greatly restricted in military and civil aspects,so there is a practical significance for the research on the wind resistance of the single rotor UAV under the disturbance by the gust.In this thesis,the wind tunnel experiment data are pretreated via the use of Matlab software,and the sixth-order wind influence function is reduced to the second-order polynomial under a low speed and the fourth order polynomial under a high speed.Then in the consideration of wind interference under the conditions of mathematical modeling,access to wind interference and aerical force and the relationship,access to wind interference and unmanned aerial force and the relationship between the forces.In the environment of Matlab,the wind tunnel test data is pretreated and brought into the wind influence function of low speed flight,and the results of the low-speed flight parameters and experimental results show that the second-order polynomial of low-speed flight is effective and feasible.The simulation results of different wind speed and different pitch are compared with the experimental results,and the reliability of the simulation experiment is verified.In this paper,the Ansys/Proe simulation software is used to model the flow field of the rotor and the flow field of the rotor and the fuselage.The rotor and the fuselage flow field will interfere with each other,so it is necessary to simulate the flow field of the rotor/fuselage assembly.The force and torque of individual rotor and individual fuselage and rotor/fuselage assemblies with wind speed and pitch as the variables indicate that the rotor and the fuselage flow field interfere with each other,especially for the rotor lift and pitch torque of the gr eatest impact,followed by the fuselage roll torque and the rotor lateral force also interfere.The results of the simulation are brought into the fourth order polynomial under high speed.The verification results show that the fourth order polynomial is more reliable.Finally,the optimized polynomial of this paper describes the function of force and moment in each direction.On this basis,the design of single-rotor UAV flight controller will have better wind resistance.