An Attitude Control Method for Flexible Spacecraft Based on Finite Time Friction Estimation

A flexible spacecraft and a control method technology, applied in the aerospace field, can solve the problems of difficulty in achieving attitude control, affecting the spacecraft attitude control system, difficult to stabilize the spacecraft system, etc., and achieve the effect of high-precision attitude control

CN105938368BActive Publication Date: 2019-01-15BEIHANG UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Publication Date
2019-01-15

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Abstract

The invention provides a flexible spacecraft attitude control method based on limited time friction estimation. The control method comprises the following steps: a, introducing spacecraft flywheel friction interference into an spacecraft dynamic system, and establishing a flexible spacecraft dynamic system sigma1 with the flywheel friction interference; b, converting the flexible spacecraft dynamic system sigma1 with the flywheel friction interference into a state space form; c, constructing a flywheel friction interference estimator; d, constructing a flexible accessory vibration interference observer; and e, compounding the flywheel friction interference estimator in the step c and the flexible accessory vibration interference observer in the step d with a nominal controller so as to obtain a composite controller which compensates flywheel friction through an estimated value of flywheel friction torque and compensates vibration interference of a flexible accessory through an estimated value of the vibration interference of the flexible accessory.
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Description

technical field

[0001] The invention relates to the field of aerospace technology, in particular to a method for controlling the attitude of a flexible spacecraft based on finite-time friction estimation. Background technique

[0002] The spacecraft attitude control system is an important part of many systems of the spacecraft. The accuracy, stability and reliability of the spacecraft attitude control are the key technologies in the process of spacecraft development. In recent years, the tasks that spacecraft need to undertake have become more and more complex, which makes the demand for power continue to increase. Therefore, it is necessary to have a larger area of ​​solar panels to meet the needs of the mission. The requirements are getting higher and higher, and antennas with larger structures need to be designed as much as possible to complete data exchange and communication. These requirements have made the accessories of spacecraft more and more large. In terms of lau...

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Embodiment Construction

[0045] The objects and functions of the present invention and methods for achieving the objects and functions will be clarified by referring to the exemplary embodiments. However, the present invention is not limited to the exemplary embodiments disclosed below; it can be implemented in various forms. The essence of the description is only to help those skilled in the relevant art comprehensively understand the specific details of the present invention.

[0046] Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. In the drawings, the same reference numerals represent the same or similar components, or the same or similar steps.

[0047] The present invention provides a flexible spacecraft attitude control method based on finite-time friction estimation, such as figure 1 Shown is the design flow chart of the flexible spacecraft attitude control method based on finite-time friction estimation of the present invention...