Uydu Yönelim Denetimi

Abstract

In this work, attitude control problem of satellites which are assumed to be as rigidbodies is addressed. Satellite attitude is represented in terms of quaternions. Due tothe nonlinear nature of satellites and in the case of large angular maneuvers, attitudecontrol is achieved via nonlinear controllers. Quaternion feedback controller, PD+controller, quaternion based backstepping controller and sliding mode controller areused for attitude control in this work. These controllers, which are all nonlinear innature, are used to control the attitude of ESEO (European Student Earth Orbiter )satellite which is a Low Earth Orbit (LEO) satellite. It is commanded for satellite tomaneuver as rest-to-rest and to track desired attitude in the presence and absenceof noise. By a simulation study, it is shown that the controllers used in this workperform well.