Satellite formation flying with input saturation: An LMI approach

In this paper, we consider a relative position control problem for a satellite formation flying system in a noncoplarnar and elliptical orbit. It is assumed that the angular rate and angular acceleration are not known, but they are bounded. The system dynamics is designed with the bounded uncertain parameters. In the presence of input saturation, we develop a state feedback controller that guarantees stability of the system. Linear matrix inequality (LMI) conditions are proposed to design the feedback controller. Finally, numerical simulation is presented to demonstrate the validity of the proposed controller.