Attitude stabilization of spacecraft simulator based on modified constrained feedback linearization model predictive control

This paper aims to discuss the approach of constrained modified feedback linearization model predictive control for spacecraft simulator. By utilizing high accuracy and properties (MPC), an optimum MPC is designed linearized system. The composite controller has ability both attitude angular velocity reaction wheels (i.e. steering momentum zero at end maneuver). simulation experimental results demonstrate that proposed hybrid insignificant calculative cost facilitates perform regulation maneuver with sufficient precision in presence external torques actuator saturations.