Calculation and Experimental Verification of Static Thrust Performance of Rotor UAV Propeller

According to the requirements of the propeller design for rotor unmanned aerial vehicle(UAV), the engineering calculation method of the static thrust performance for small propeller of rotor UAV is studied in this paper, and the measurement and control system is established based on the theory of virtual instrument. Vortex theory is adopted for the calculation of the static thrust performance. The test platform of propeller static thrust is established using the graphical modeling software LabVIEW. The calculation results are compared with the experimental data for verification. Analysis result shows that the trend of calculation results matches the trend of experimental data, the maximum average relative error is less than 10%. The calculation has high accuracy and can be trusted.