基于角加速度反馈的控制力矩陀螺框架转速控制方法OA

The control moment gyroscope(CMG)serves as a critical component within the attitude control sys-tem of spacecraft.CMG is affected by the interference of multi-source coupling torque during its actual opera-tion,which affects the accuracy of the CMG gimbal control system.A gimbal rate control scheme for CMG sys-tem is designed based on angular acceleration feedback combined with a tracking differentiator.In the feedback loop of the CMG gimbal control system,the compensation current of the disturbance torque is calculated through angular acceleration and current acquisition values of CMG gimbal.A numerical integration method based on tracking differentiator is adopted for calculation of angular acceleration of CMG gimbal,which uses nu-merical integration to avoid the problem of noise signal amplification caused by traditional differential methods.Both simulation and experimental analyses demonstrate that the proposed method can effectively mitigates the im-pact of disturbance torque on the CMG gimbal rate control system,thereby notably enhances its control accuracy.