Spacecraft attitude control method based on event triggering

Abstract

The application discloses a spacecraft finite time sliding mode attitude control method based on a dynamic threshold trigger, first, through a quaternion-based kinematics and dynamics model, an attitude tracking error model of the spacecraft is established. Next, a finite time non-singular sliding mode surface is designed, and the centralized disturbance in the system is approximately processed in combination with a fuzzy logic system, so that the anti-interference ability and control precision of the system are improved. Finally, through a dynamic threshold trigger mechanism, a finite time attitude tracking controller is designed, and the control update is triggered only when the system state change reaches a preset threshold, so that the communication and calculation burden are significantly reduced, and the system is ensured to converge and remain stable within a limited time. Through the introduction of the dynamic threshold trigger mechanism and the finite time sliding mode control technology, the control update frequency is simplified, the accurate processing of the centralized disturbance is realized in combination with the fuzzy logic system, so that the control precision and stability of the system are improved, and solid technical support is provided for the spacecraft attitude control.

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