SATELLITE ATTITUDE TRACKING BY QUATERNION-BASED BACKSTEPPING

Abstract In this paper a result on attitude tracking control of a micro satellite by integrator backstepping based on quaternion feedback is presented, and the controller is shown to render the system equilibrium point UGAS by application of the LaSalle-Yoshizawa theorem. This is a part of a study of possible control methods for the spacecraft ESEO, a spacecraft included in the SSETI project initiated by ESA. ESEO is actuated by four reaction control thrusters and one reaction wheel, and simulation results based on data from the satellite are presented.

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