Nonlinear model predictive control for large angle attitude maneuver of spacecraft with RW and RCS

This paper studies nonlinear model predictive control (MPC) for spacecraft attitude maneuver problems when continuous inputs with saturation by reaction wheels (RW) and quantized inputs by reaction control systems (RCS) are used. After providing optimization algorithms based on branch and bound methods, we derive linear matrix inequality (LMI) conditions to ensure the input-to-state stability (ISS) for RCS case and the asymptotic stability (AS) for RW case. The results are evaluated for high-rate large angle attitude switching maneuver problems of an astronomical satellite.