Near minimum-time feedback attitude control with multiple saturation constraints for satellites

A near minimum time feedback control law is proposed for the agile satellite attitude control system. The real time controller is formed by specially designed cascaded subunits. Based on this, the rapid attitude maneuvering can be applied in tasks including the move to move case. The near optimal property of that is guaranteed by the rapid dynamic response with a modified bang-bang control logic while simultaneously ensuring non-saturation properties on 3-Axis. The near optimal method is utilized for an online attitude planning, and the generated attitude maneuver path in real time is tracked by a nonlinear back-stepping controller with its improved dynamic performance and by which the united closed loop control is implemented. Numerical simulations are conducted to verify the effectiveness of the proposed control strategy.