Structural Design and Simulation of an Electrically Driven Heavy-Duty Six-rotor UAV

The structural design of a multi-rotor unmanned aerial vehicle (UAV) is a crucial aspect of UAV development. Based on the performance requirements of a heavy-duty six-rotor UAV, this study designs an electrically driven six-rotor UAV with a maximum payload capacity of 270 kg and high structural strength. A finite element model of the UAV structure was established, and both static and dynamic characteristics of the entire body were analyzed under actual working conditions. The simulation results indicate that the maximum compressive strain, tensile strain, and shear strain in the UAV’s arms are $4450 \mu \varepsilon, 4890 \mu \varepsilon$, and $3720 \mu \varepsilon$, respectively, all significantly lower than the allowable stress of the composite material, thereby meeting strength requirements. The maximum stress of the fuselage, landing gear, connectors, and connection plates in metal components were $410 \mathrm{MPa}, 56.8 \mathrm{MPa}$, 288 MPa, and 144 MPa, respectively, all within the limit values of the metal materials. The findings provide a new approach to the overall design of electrically driven heavy-duty six-rotor UAVs.