Abstract
The spacecraft attitude tracking control problem with limited communication is addressed by employing event-triggered based sliding mode control theory. The attitude dynamics are directly developed on the Special Orthogonal Group SO(3), and singularities and ambiguities associated with other attitude representations are avoided successfully, taking model uncertainties and external disturbances into consideration. Based on the developed model, an adaptive eventtriggered sliding mode controller is designed to ensure the closed-loop system that is uniformly ultimately bounded, by using fuzzy logic theory to deal with the disturbance. Due to the application of the event-triggered theory, the control signal is only updated and transmitted at some discrete instants. Therefore, the communication burden is decreased significantly. Finally, numerical simulations are conducted to demonstrate the effectiveness of the proposed control method.
Keywords: Communication burden, Event-triggered, SO(3), Fuzzy logic theory, Spacecraft attitude tracking control.
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