A proportional-integral event-triggered spacecraft attitude control method

Abstract

The invention discloses a proportional-integral event-triggered spacecraft attitude control method. First, a satellite attitude tracking error system model is constructed based on a quaternion-based satellite attitude dynamics and kinematics model; second, a satellite attitude tracking error system model is constructed according to the satellite attitude. , determine the extended state of the attitude tracking error system, and design an extended state observer; 3. Use the extended state observer to obtain the system observation state, and design a feedback controller based on the system observation state; 4. Based on the sampling error of the output signal of the feedback controller, design The proportional-integral event trigger strategy is used to decide whether to update the control signal of the spacecraft attitude; the invention can resist the interference of external environment interference and internal uncertainty on the spacecraft attitude, and at the same time reduce unnecessary signal transmission in the spacecraft attitude control, The attitude control performance is guaranteed while saving limited on-board communication resources.

Description

technical field [0001] The invention belongs to the technical field of event-triggered control and spacecraft attitude control, and in particular relates to a proportional-integral event-triggered spacecraft attitude control method. Background technique [0002] Attitude control of spacecraft is a key prerequisite for spacecraft to perform various tasks smoothly in orbit. In-orbit spacecraft, in order to complete various tasks, need to operate in a certain reference attitude to ensure that the payload on the spacecraft can work. At the same time, due to various space environment perturbations and the influence of the uncertainty of the spacecraft itself, the attitude of the spacecraft is easily changed due to interference, and regular control is required to maintain the attitude stability. With the development of spacecraft formation technology, the need for stable communication between formation spacecraft puts forward higher requirements for spacecraft attitude control. ...

AI Technical Summary

Problems solved by technology

Most of the existing spacecraft have limited resources on the planet, and the kinematics and dynamics equations of rigid spacecraft have highly coupled nonlinear characteristics, and the control system may be affected by external disturbances and internal uncertainties, which makes the spacecraft’s high Precision attitude control is extremely challenging

[0003] Aiming at considering event-triggered spacecraft attitude control methods, according to investigation and understanding, the currently disclosed prior art is as follows: the invention patent application publication number CN109471448 discloses an event-driven flexible spacecraft attitude control method, but the method requires The design event trigger conditions are relatively complex, and the existence of external interference is not considered; the invention patent application publication number CN107589671 discloses an event-driven satellite attitude control method, which uses mixed event-driven conditions, but also does not consider external interference The existing situation; the invention patent of application publication number CN112363522 discloses a networked spacecraft attitude control method based on hybrid forced sensors, which uses a static event trigger mechanism to avoid the transmission of a large amount of data in the observer, and overcomes the The influence of nonlinear uncertain items is eliminated, and the robustness of the spacecraft attitude tracking system is improved

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