Flywheel fault identification and adjustment method for rigid spacecraft attitude control system

A technology of fault identification and adjustment method, which is applied in the field of aerospace flight control, can solve problems such as control input saturation and actuator efficiency loss, and achieve the effect of improved tolerance and strong robustness

Active Publication Date: 2018-11-06
NANJING UNIV OF POSTS & TELECOMM
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Problems solved by technology

[0004] Purpose of the invention: the purpose of the invention is to solve the problems of actuator efficiency loss failure and control input saturation in the existing rigid spacecraft attitude control system

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  • Flywheel fault identification and adjustment method for rigid spacecraft attitude control system
  • Flywheel fault identification and adjustment method for rigid spacecraft attitude control system
  • Flywheel fault identification and adjustment method for rigid spacecraft attitude control system

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Embodiment Construction

[0058] Now, a more detailed description will be given to specific embodiments of the present invention according to the accompanying drawings.

[0059] In order for those skilled in the art to better understand the implementation of the present invention, the present invention also provides simulation verification results of fault estimation and fault-tolerant control using Matlab2017a software.

[0060] Such as figure 1 As shown, when the actuator in the attitude system has an efficiency loss fault and a control input saturation, in order to stabilize the attitude of the rigid spacecraft, a fault estimation module is established through a sliding mode observer to accurately estimate the fault in real time, and further use the fault estimation information Design a fault-tolerant controller to improve the tolerance to faults of the rigid spacecraft attitude control system.

[0061] The invention is a method for fault-tolerant control of a rigid spacecraft attitude system, comp...

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Abstract

The invention discloses a flywheel fault identification and adjustment method for a rigid spacecraft attitude control system, and solves the problem of fault-tolerant control scheme design of the spacecraft attitude control system in the presence of an efficiency loss fault and a control input saturation condition of an actuator or a reaction flywheel. A sliding mode fault estimation observer is designed for the fault attitude system. An estimated value of the actuator efficiency loss fault is obtained by the designed self-adaptive parameter updating algorithm. Then, a attitude fault-tolerantcontroller using the sliding mode control scheme is designed, which can ensure the asymptotic stability of the closed-loop attitude system in the presence of the efficiency damage fault and control input saturation of the actuator. Finally, simulation verifies the effectiveness of the fault-tolerant method of the invention. The method enables a stable attitude of the rigid spacecraft attitude system in the event of the efficiency loss fault and control input saturation of the actuator, and can fully take the uncertainty of the rigid spacecraft model and the effects of external disturbances onthe rigid spacecraft model into account.

Description

technical field [0001] The field of the present invention is aerospace flight control, and the specific content of the invention is a new fault-tolerant control method based on fault adjustment under the situation of actuator efficiency loss fault and input saturation in a rigid spacecraft attitude control system. Background technique [0002] A stable spacecraft attitude control system is one of the important conditions to ensure the normal operation of the spacecraft. The dynamics of rigid spacecraft are subject to highly nonlinear actuator saturation, reactive flywheel friction, space environment disturbances, inertia matrix uncertainties and even actuator failures. Due to the inherent uncertainty and external interference, especially in the severe case of actuator failure in the attitude system, the accuracy of attitude control will decrease, and even cause the system to be unstable, resulting in accidents. Therefore, the attitude controller must have strong robustness ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 高志峰张孝波钱默抒蒋国平林金星白浪
Owner NANJING UNIV OF POSTS & TELECOMM
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