Dynamic Analysis of the Fuselage of a Four-Rotor Unmanned Aerial Vehicle

Abstract

The four-rotor unmanned aerial vehicle has a light and simple structure, convenient control and broad application prospects, so it has great research significance. In order to study the vibration and response characteristics of the four-rotor unmanned aerial vehicle fuselage, the Ansys Workbench was used to analyze the fuselage. First, the fuselage structure is modeled and modal analysis is performed. The results show that the excitation frequency of the four-rotor unmanned aerial vehicle avoids the natural frequency of the fuselage and avoids the occurrence of resonance. Based on the modal analysis, the harmonic response analysis is carried out. The results show that the fuselage can overcome the harmful vibration caused by the cyclic load generated by the rotor, which provides a theoretical reference and basis for the design and improvement of the fourrotor unmanned aerial vehicle.