Momentum Management of a Hybrid Spacecraft Attitude Control System

In this research, a method for controlling the angu-lar momentum of a spacecraft is proposed for a hybrid attitude control system that includes a RW and a cluster of Control Moment Gyros for the nominal work of three-axis attitude control. Two performance indices are set: the newly designed RW saturation index and the CMG singularity index. In the event that the reaction wheel approaches the maximum angular velocity, the saturation index initiates the desaturation requirement. The weighting matrix of the weighted pseudoinverse steering rule has these indices organized in a combined version that ensures the cluster of CMGs avoids singularity while preventing the RW from saturation. To illustrate the potential of the suggested method, simulation scenarios are conducted.