Sliding mode attitude controller design for nonlinear flexible geosynchronous satellite with thrust jets

In this paper, the attitude dynamics and effects of flexible solar arrays of a three axes stabilized geosynchronous communication satellite are studied. A spacecraft is assumed to be controlled externally with small attitude thrust jets. A new combined variable structure P+relay chattering-free controller with optimal sliding manifold is designed which successfully stabilizes the nonlinear attitude dynamics of the spacecraft with open solar arrays for bounded space of attitude angles. The discussions and performances of proposed attitude sliding mode controller are stated and supported with a large attitude angle maneuver simulation.