Abstract:  The combined configuration solution of momentum wheels and control methods for large satellites with high attitude stability performance were studied in this paper because the attitude maneuver duration time was too long to satisfy task requirements due to the small output torque of the ordinary momentum wheels.First of all，a combined configuration solution of momentum wheels was proposed by adding a series of large-torque flywheels along the roll axis to an ordinary momentum wheel assembly，and a corresponding control approach was designed to integrate the closed-loop feedback control of the ordinary momentum wheels with the open-loop feedforward control of the large-torque flywheels.Meanwhile，a feedforward torque distribution law for the large-torque flywheels was adopted to realize the efficient management of the angular momentum of large-torque flywheels，where the output torque was proportional to each flywheel providable angular momentum；together with an angular momentum servo tracking control method，the deviation of the output torque from the command torque caused by the flywheel model uncertainty was mitigated simultaneously.Furthermore，to ensure high attitude stability realization，a disturbance estimator was utilized to accomplish the real time disturbance torque compensation.At last，the effectiveness of the proposed solution and methods was illustrated by the in-orbit application.The application shows that the stabilization time of roll-axis maneuver reduces more than 100s，and the attitude stability error during non-maneuver period is less than 3.75×10^-5（°）/s.

Key words:  , attitude control；hybrid flywheel configuration；feedforward control；momentum wheel；large-torque flywheel