LPV design for a space vehicle attitude control benchmark problem

This paper is concerned with the design of quaternion-based, attitude tracking controller for a rigid spacecraft under a large angle maneuver. A new design technique is proposed, which is based on the decomposition of kinematics control and dynamics control, using linear parameter-varying (LPV) synthesis framework. The proposed LPV controllers ensure asymptotic attitude tracking. In addition, this two-step LPV design greatly reduce the computation effort than that of standard LPV synthesis. Non-linear simulation demonstrates the effectiveness of the proposed method.