Backstepping Sliding Mode Method for Attitude Stabilization Control of Small Satellites

Abstract

To address the problem that the attitude of a rigid satellite in orbit is susceptible to external disturbing moments, a control method based on the backstepping sliding mode method is proposed, which has strong robustness and anti-disturbance capability. Firstly, the coupling term in the mathematical model of satellite attitude is eliminated by using the backstepping method, secondly, the sliding mode control law is designed to reduce the sensitivity of the system to the external disturbance moment change and accelerate the response speed of the system, and the stability of the system is proved by using Lyapunov stability theory. Finally, the effectiveness and superiority of the rigid satellite attitude control based on the backstepping sliding mode method are verified by simulation.