Attitude control method of flexible spacecraft

A flexible spacecraft and attitude control technology, which is applied to space navigation equipment, space navigation vehicles, space vehicle guidance devices, etc., can solve various types of interference and other problems, meet dissipation performance and save communication resources , Improve the effect of anti-jamming performance

Active Publication Date: 2022-02-22
QUFU NORMAL UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In addition, during the mission of the spacecraft, it is inevitable to suffer from various types of interference
Therefore, attitude control of flexible spacecraft systems is clearly a challenging task

Method used

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  • Attitude control method of flexible spacecraft
  • Attitude control method of flexible spacecraft
  • Attitude control method of flexible spacecraft

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Embodiment Construction

[0043] Specific embodiments of the present invention are described in detail below, but it should be understood that the protection scope of the present invention is not limited by the specific embodiments.

[0044] Unless expressly stated otherwise, throughout the specification and claims, the term "comprise" or variations thereof such as "includes" or "includes" and the like will be understood to include the stated elements or constituents, and not Other elements or other components are not excluded.

[0045] Such as figure 1 As shown, the attitude control method of a flexible spacecraft disclosed by the present invention comprises the following steps:

[0046] S100, establishing a kinematics model and a dynamics model of a flexible spacecraft with multi-source interference, the multi-source interference includes the L 2The first disturbance of the space and the second disturbance described by the exogenous nonlinear system.

[0047] Specifically, in this step, the kinema...

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Abstract

The invention discloses an attitude control method of a flexible spacecraft. The attitude control method comprises the following steps: establishing a kinematics model and a dynamics model of the flexible spacecraft with multi-source interference; adopting two groups of T-S fuzzy models to perform modeling on second interference described by the flexible spacecraft system and the exogenous nonlinear system; constructing a flexible vibration observer for estimating a flexible mode, and constructing a fuzzy disturbance observer with an asynchronous prerequisite variable for obtaining an estimated value of external disturbance modeled by the T-S fuzzy model, and respectively obtaining a flexible mode error system and a disturbance error system; and based on the output value of the observer, designing an event-triggered anti-interference controller for controlling the attitude of the flexible spacecraft. According to the method, the influence of flexible vibration and multi-source interference on the flexible spacecraft can be effectively reduced, vibration suppression and attitude stabilization are realized, the anti-interference capability of the spacecraft is improved, communication resources can be saved, and the method is suitable for attitude control of the flexible spacecraft.

Description

technical field [0001] The invention relates to the technical field of control of flexible spacecraft, in particular to an attitude control method of a flexible spacecraft. Background technique [0002] For nearly half a century, flexible spacecraft have played great advantages in deep space exploration missions. Therefore, the problem of attitude stabilization of spacecraft systems has important practical significance and has received considerable attention. Compared with rigid spacecraft, flexible spacecraft has certain advantages in achieving rapid attitude maneuvers and has a longer service life. [0003] However, the flexible part causes elastic vibrations to the spacecraft during launch. This could compromise the stability and control performance of spacecraft systems. In addition, spacecraft systems also have some notable features: high nonlinearity and strong coupling. These properties are difficult problems in the design of attitude controllers. In addition, du...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/244B64G1/245Y02T90/00
Inventor 孙海滨王亚文侯林林宗广灯杨东
Owner QUFU NORMAL UNIV
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