Characteristic analyzes, experimental testing and control for attitude system of QUAV under disturbance

Abstract

The disturbance influences the dynamic characteristics of the quadrotor unmanned aerial vehicle (QUAV), especially the stability. With the disturbance, the study of characteristics and controller design is challenging. In this paper, an attitude system of a QUAV with disturbance and gyroscopic effect is developed. The disturbed QUAV attitude system dynamics influenced by the rotor speeds are analyzed via multi-parameter bifurcation diagrams. The chaotic parameter area in which the QUAV is in an abnormal vibration state is plotted, guiding the design of the fuselage structure and controller of the QUAV. The transient chaos characterizing chaos within a long period but eventually becoming periodic is found in the system. The chaotic phenomenon of the angular velocity trajectory of the QUAV is verified by obtaining the positive Lyapunov exponent using the experimental data. A back-stepping sliding mode controller is designed, and the stability of the closed system is proved via the Lyapunov method. Numerical simulations verify the effectiveness of controlling the QUAV. The designed controller is effective for suppressing chaos. The stability of the back-stepping sliding mode controller is superior to that of the PID controller is verified via numerical simulations.