High-precision and high-performance attitude fault-tolerant control method, device and computer storage medium for earth remote sensing satellites
A remote sensing satellite and fault-tolerant control technology, applied in attitude control, vehicle position/route/altitude control, control/adjustment system, etc., can solve the problems of reducing the overall rigidity of the spacecraft, reducing the accuracy of attitude pointing, model nonlinearity, etc., to achieve Effect of overcoming model parameter uncertainty and external interference, ensuring reliability and safety, and high-safety control
Active Publication Date: 2022-08-02
HARBIN INST OF TECH
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Problems solved by technology
[0005] For earth remote sensing observation satellites, due to the nonlinearity of the model, parameter uncertainty, measurement error and unknown environmental interference, it is difficult to involve a high-performance spacecraft attitude controller
In addition, the spacecraft may carry large appendages with low stiffness and light weight, such as large deployable antennas and solar panels, etc. These structures reduce the overall rigidity of the spacecraft, resulting in the phenomenon of flexibility
In particular, the attitude maneuver of the spacecraft platform will inevitably excite the vibration of the flexible attachment, which will affect the state of the spacecraft through the rotation of the hinge, thereby reducing the attitude pointing accuracy
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[0039] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.
[0040] Usually, in the design process of spacecraft attitude controller, flexible accessories need to be considered to compensate for the adverse effects of rigid-flexible coupling. The vibration term of the flexible attachment can be substituted into the attitude dynamics model of the spacecraft through the coupling equation and considered as an uncertainty. External disturbances, measurement errors, and model uncertainties are then classified as integrated uncertainties. These uncertainties can lead to imprecise pointing of the spacecraft payload and even lead to instability of the spacecraft platform. Usually, however, the integrated perturbation cannot be measured directly. To solve this problem, a feasible solution is to use the perturbation observer technique ...
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The embodiment of the present invention discloses a high-precision and high-performance attitude fault-tolerant control method, device and computer storage medium for an earth remote sensing satellite; the method may include: obtaining the described The error kinematic equation of the earth remote sensing satellite; the rigid-flexible coupled attitude dynamics equation of the earth remote sensing satellite is obtained based on the Lagrangian method; based on the uncertainty of the model and the error kinematic equation of the earth remote sensing satellite The measurement kinematics model and dynamic model of the earth remote sensing satellite are obtained respectively from the rigid-flexible coupled attitude dynamics equation of the earth remote sensing satellite; The mode disturbance observer FTISMDO estimates the integrated uncertainty in the measurement kinematic model and dynamic model of the earth remote sensing satellite; according to the estimated integrated uncertainty, the earth remote sensing satellite is designed by backstepping Attitude anti-disturbance fault-tolerant controller.
Description
[0001] CROSS-REFERENCE TO RELATED APPLICATIONS [0002] This application is based on the Chinese patent application with the application number of 202010019159.3, the application date of January 10, 2020, and the title of the invention, "the high-precision and high-performance attitude control method, device and computer storage medium for earth remote sensing satellites", and requires the The priority of the Chinese patent application, the entire content of which is incorporated herein by reference. technical field [0003] The embodiments of the present invention relate to the technical field of spacecraft attitude control, and in particular, to a high-precision and high-performance attitude fault-tolerant control method, device and computer storage medium for an earth remote sensing satellite. Background technique [0004] At present, great progress has been made in space science and technology, and complex space missions, such as space rendezvous and docking, earth remot...
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IPC IPC(8): G05D1/08
CPCG05D1/0808
Inventor 王峰刘明曹喜滨吴凡邱实耿云海苗悦
Owner HARBIN INST OF TECH