Control of Hybrid Unmanned Aerial Vehicle Motion in Transitional Modes

Abstract

Results of investigations of the flight control system for a hybrid unmanned aerial vehicle prototype in transitional modes 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 take-off, hovering, and landing, as well as a control subsystem operating in transitional modes from quadrotor to aircraft modes and back.