Abstract:In response to the singular phenomena that are prone to occur during attitude maneuvers of the application control moment gyroscope (CMG) satellites, an attitude dynamics equation is established with CMG speed commands as input. The established state space equation is discretized, and optimization calculation indicators are designed. Online optimization calculation of input speed commands is used to minimize torque errors caused by commonly used CMG control laws. A predictive control algorithm based on optimization iteration is designed to provide an attitude maneuver feedback controller with a closed-loop structure. In order to reduce the computational burden of online optimization and minimize the number of optimization calculations, a satellite attitude maneuver predictive controller with an event-triggered mechanism is designed, the controller can avoid CMG singularity and control satellite rapid maneuver, and effectively reduces the burden of in-orbit calculation on this basis. Through the simulation of the event-triggered attitude maneuver prediction controller for rigid body satellites, it is further demonstrated that this controller has the remarkable ability to significantly reduce the online computing burden.