Attitude control based on inverse system for a spacecraft with zero-momentum wheels

In order to satisfy celerity and veracity of spacraft attitude responses,an attitude control method based on inverse system for a spacecraft with zero-momentum wheels is discussed.The spacecraft attitude model with wheel dynamics and its compensator was viewed as a generalized plant,and an attitude controller,which combined inverse system method with internal model principal,was presented.The friction effect for the momentum wheel was analyzed and a low-speed and high-speed compensator based on an observer was designed.Some simulations about the method were done under the circumstance of changing inertia and adding disturbances.The generalized model was decoupled into three single-input-single-output systems via inverse system method based on state feedback.The closed loop controller based on internal model principal remedied nonideal decoupling.The compensator mades attitude response be quicker.Simulation results show that the combined controller is valid to control spacecraft attitude,and system robustness is strong for inertia parameters and disturbances.