Finite modal vibration control of rigid–flexible satellites

In this research, we propose a novel and comprehensive control strategy for vibration suppression of rigid–flexible satellites during attitude maneuvers. Based on the vibration dynamics, the number of controlled vibration modes is correlated with the number of actuators and sensors, and their influence on vibration suppression is initially analyzed from the perspective of the model. The deployment of the actuators and sensors is discussed in terms of both control energy and model error, with optimization performed to achieve the optimal deployment using the corresponding criterion functions. Considering the small deformation assumption employed in the modeling process, the improved prescribed performance function is applied in the finite modal controller to guarantee the system consistently adheres to the small deformation assumption. Eventually, numerical simulations are presented to validate the effectiveness of the finite modal vibration control and to further illustrate the relationship between the number of controlled modes, the deployment of the actuators and sensors, and the control effect.