Hover Control of New type ducted aircraft

Abstract

In this paper, a new type of foldable winged unmanned aerial vehicle is designed, and the structure of the aircraft is analyzed. The dynamic model is established and an improved sliding mode control algorithm is used to control the attitude of the aircraft. In addition, a centroid position control method using attitude compensation is designed for the coupling characteristics of this aircraft. The simulation proves that the attitude and position of the new aircraft can be effectively controlled.