Résumé:
In the past few decades till now, satellites are considered one of the hottest topics featuring Advanced technology and modern control designs, due to its vast utility in multiple domains. critically, control systems have helped satellite's importance continue its growth by the day. The idea of a good controller in a satellite (attitude-wise) is to keep it as stable as possible throughout its journey around the earth maintaining a good attitude precision with acceptable energy consumption. This thesis is concerned with designing an attitude controller for a chosen satellite using linear and nonlinear control theories. initially, the mathematical model of the satellite's dynamics is derived, then, a background review of the linear and
nonlinear control theories that are used in the controller design, a multiinput multi-output PID (Proportional Integral Derivative) as linear, and feedback linearization as nonlinear. further, the thesis investigates an optimization method for the PID controller being particle swarm optimization. The designed controller’s performance is tested and compared.
