Adaptive Event-Triggered Attitude Tracking Control for Spacecraft

摘要

An adaptive attitude tracking control law based on an event-triggered control strategy is proposed to discuss the problem of plug-and-play satellite attitude tracking maneuvers with limited data transmission among independent models. In this scheme, the controller is updated aperiodically only in the case that a designed event-triggered condition is satisfied, so unnecessary communication among modules can be avoided and the sampling frequency is optimized. Also, the control problem is under the condition of inaccurate knowledge of inertial matrix. Considering the uncertainty of system parameter, inertia matrix, an adaptive control is used to avoid using the real value of inertia matrix. The proposed control scheme not only ensure stability of attitude tracking closedloop control system but also a positive lower bound between adjacent triggered instant to avoid Zeno behavior. Finally, the numerical simulation results verify the effectiveness of the designed controller.