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Adaptive spacecraft attitude tracking control method based on event trigger mechanism

A technology of event triggering and tracking control, applied in the fields of adaptive spacecraft attitude tracking control and modular spacecraft attitude tracking control, which can solve problems such as waste of network resources, wear and tear of actuators, and inappropriateness

Active Publication Date: 2018-08-24
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, in this way, whether it is necessary or not, the actuator and the controller must communicate and update the control algorithm at each sampling time, which will cause a waste of network resources and wear of the actuator
Obviously, this method is inappropriate under the condition of limited network resources

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  • Adaptive spacecraft attitude tracking control method based on event trigger mechanism
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Embodiment Construction

[0034] In order to understand the above-mentioned purpose, features and advantages of the present invention more clearly, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that, in the case of no conflict, the embodiments of the present application and the features in the embodiments can be combined with each other.

[0035] In the following description, many specific details are set forth in order to fully understand the present invention. However, the present invention can also be implemented in other ways different from those described here. Therefore, the protection scope of the present invention is not limited by the specific details disclosed below. EXAMPLE LIMITATIONS.

[0036] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0037] Such as figure 1 As shown, the steps of an adaptive spacecraft...

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Abstract

The invention relates to an adaptive spacecraft attitude tracking control method based on the event trigger mechanism. The method comprises steps that a spacecraft dynamics model with external disturbance and a relative attitude tracking error model are established; the event triggering mechanism applied to control is defined, and the relationship between a transmission control torque signal and acontrol torque signal designed by a controller is constructed based on the event triggering mechanism; based on the spacecraft dynamics model and a relative attitude tracking error model establishedin the first step and the relationship constructed between the transmission control torque signal and the control torque signal designed by the controller based on the event triggering mechanism, thereverse step method is utilized to introduce boundary estimates and auxiliary signals, and event-triggered adaptive control of the spacecraft attitude is carried out. The method has advantages of strong anti-interference and small calculation amount, communication traffic of the controller and the update frequency of a control signal can be effectively reduced, and the method is suitable for attitude control on modular spacecrafts with the limited transmission capacity of the wireless network.

Description

technical field [0001] The invention relates to an adaptive spacecraft attitude tracking control method based on an event trigger mechanism, which is mainly applied to the attitude tracking control of modular spacecraft and belongs to the technical field of spacecraft control. Background technique [0002] In recent years, attention has been paid to modular spacecraft. Modular spacecraft adopts a modular open network architecture. Using the basic idea of ​​plug-and-play system, each component of the spacecraft is modularized and assembled, which can reduce the cost of the spacecraft. Speeds up assembly and facilitates easy removal and replacement of defective or obsolete components. The core technology of modular spacecraft is wireless data communication and wireless power transmission, which is different from the traditional cable interconnection that is bulky, bulky, and inflexible. Under this technology, all functional parts of the spacecraft are independent of each other...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 胡庆雷杨晨郭雷王陈亮
Owner BEIHANG UNIV
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