Control of hybrid aerial vehicle motion in transitional regimes
Results of studying the system used to control the flight of a hybrid aerial vehicle prototype in transitional regimes are presented. The hybrid vehicle is equipped with a quadrotor and main propulsion units. The control system developed in the study includes subsystems for attitude stabilization, vertical takeoff, hovering, and landing, as well as a control subsystem operating in transitional regimes from quadrotor to aircraft modes and back.