Satellite attitude control by quaternion-based backstepping

Abstract

In this paper a result on attitude control of a microsatellite by integrator backstepping based on quaternion feedback is presented, and the controller is shown to make the closed loop equilibrium points asymptotic stable in the sense of Lyapunov. This is a part of a study of possible control methods for the spacecraft European Student Earth Orbiter (ESEO), a spacecraft included in the Student Space Exploration and Technology Initiative (SSETI) project initiated by ESA. The spacecraft is actuated by four reaction control thrusters and one reaction wheel, and simulation results based on data from the satellite are presented.