Propulsion optimization of a quadcopter in forward state

A propulsion system suitable for the forward state of a quadcopter is optimally designed in this study. The forward model of the rotor in tilt flow is established using a linear regression method to process the aerodynamics data acquired from the empirical blade element momentum theory (BEMT). Fuselage model is constructed by high fidelity computational fluid dynamics (CFD) method. Based on the models, the performance of the UAV can be derived precisely and quickly with the propulsion system parameters. Then, the propulsion system is optimized to better realize the forward flight endurance by using genetic intelligent optimization algorithm. Finally, wind-tunnel tests are conducted and the results indicate that the optimal propulsion system can efficiently improve the forward flight endurance.