Aerodynamic Characteristics Analysis And Wind Tunnel Experimental Study Of A Four Rotor UAV

Multi rotor unmanned aerial vehicles are widely used in industries such as military,agriculture,forestry,and performance activities.Compared to fixed wing drones and single rotor drones,their principles and aerodynamic characteristics are more complex.There is mutual interference between the rotors,and small multi rotor drones are prone to lateral interference during flight,which can cause the drone to lose balance and be difficult to control.Currently,most research focuses on the structure and flight control of multi rotor unmanned aerial vehicles.Therefore,this thesis takes quadrotor UAV as the research object,and uses CFD numerical simulation and wind tunnel test methods to study the aerodynamic characteristics of quadrotor UAV.The main research content and conclusions are as follows:Design of a self priming DC wind tunnel as an experimental platform for testing the aerodynamic performance of unmanned aerial vehicles.Based on wind tunnel theory and experimental requirements for the aerodynamic performance of unmanned aerial vehicles,a self priming direct current wind tunnel was designed,and numerical simulation analysis was conducted on the wind tunnel.The analysis results showed that the wind speed inside the tunnel was uniform and could meet the experimental requirements.Based on the analysis results,a self priming DC wind tunnel platform was built.After the construction was completed,the experimental calibration of the wind tunnel test section was carried out.The calibration results showed that the wind was most stable and could meet the experimental wind speed requirements at 0.6m at the entrance of the test section.Simulation and analysis of aerodynamic characteristics of quadrotor UAV.The geometric modeling of the quadrotor UAV is established,and the CFD numerical simulation method is determined according to the structural characteristics of the UAV.Based on the CFD numerical simulation method,the aerodynamic characteristics of the isolated rotor and quadrotor UAV under different lateral winds are simulated and analyzed by using Fluent,and the influence of different lateral winds on the lift and stability of the UAV is obtained.Wind tunnel test analysis of quadrotor UAV.The mechanical experiments of quadrotor UAV under different wind conditions were carried out in the designed self suction DC wind tunnel environment.The comparative analysis of the experimental results and simulation data showed that the test results and simulation results were basically consistent within the allowable error range,and matched with the conclusions obtained from cloud image analysis,indicating that the simulation and experiment were correct.