为减小维持大型航天器的姿态稳定和降低能量消耗的动量管理中的扰动力矩对姿态稳定的干扰,设计了周期性抑制滤波器。姿态控制的执行机构采用双框架控制力矩陀螺群(DGCMGs),应用KENNEL操纵率,使航天器执行机构的角动量在本体系的x轴分量和偏航角可达稳定,同时角动量在本体系的z轴分量和滚转角可在较小的范围内振荡。数值仿真结果验证了方案的可行性。 A periodic suppression filter is designed to reduce the disturbance of attitude stability caused by the disturbance torque in the momentum management that maintains the attitude stability of large spacecraft and reduce energy consumption. The attitude control actuator adopts double-frame control moment gyro group (DGCMGs) and KENNEL control rate to make the angular momentum of the spacecraft actuator stable in the x-axis component and yaw angle of this system. At the same time, the angular momentum in this system The z-axis component and roll angle can oscillate in a smaller range. Numerical simulation results verify the feasibility of the scheme.