A proportional-integral event-triggered spacecraft attitude control method

An event-triggered, proportional-integral technology, applied in attitude control, control/regulation systems, non-electric variable control, etc., can solve problems such as ignoring external interference, limited resources, and complex event triggering conditions, so as to overcome external interference and internal Uncertainty, reduced transmission frequency, effects of low communication rates

CN113608540BActive Publication Date: 2022-07-05BEIJING INSTITUTE OF TECHNOLOGYGY
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Publication Date
2022-07-05

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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.
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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. ...

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Embodiment Construction

[0024] The present invention will be described in detail below with reference to the accompanying drawings and embodiments.

[0025] The invention provides a proportional-integral event-triggered attitude control method, including the establishment of an attitude tracking error system model, the design of an expanded state observer, the design of a feedback control signal, and the design of a proportional-integral event-triggered mechanism. as attached figure 1 As shown, the attitude tracking error system model described by quaternion is established first; secondly, the system expansion state is defined, and the expansion state observer is designed; then the feedback controller is designed according to the observation value output by the expansion state observer, and the feedback control law is calculated; finally A proportional-integral event-triggering mechanism based on the sampling error of the control signal is designed, and whether to update the spacecraft attitude contr...