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A Coupling Control Method of Attitude and Structural Vibration of Flexible Spacecraft

A flexible spacecraft and structural vibration technology, applied in the direction of adaptive control, general control system, control/regulation system, etc., can solve problems such as system instability, improve pointing stability, suppress elastic vibration of flexible structures, The effect of fast and stable posture

Active Publication Date: 2021-10-01
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0005] The purpose of the present invention is to propose a coupling control method for the attitude and structural vibration of a flexible spacecraft, which solves the technical problem that the independent design of the two subsystems of attitude control and vibration control leads to system instability

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  • A Coupling Control Method of Attitude and Structural Vibration of Flexible Spacecraft
  • A Coupling Control Method of Attitude and Structural Vibration of Flexible Spacecraft
  • A Coupling Control Method of Attitude and Structural Vibration of Flexible Spacecraft

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Embodiment Construction

[0015] The specific implementation will be described below in conjunction with the accompanying drawings.

[0016] One, the coupling control method of a kind of flexible spacecraft attitude and structural vibration of the present invention, basic idea is aimed at containing the spacecraft of flexible structure (see figure 2 ), a coupled control method is designed based on robust control and positive position feedback control. The coupled control algorithm calculates the control input of the attitude control actuator and the vibration control actuator, and simultaneously controls the attitude and flexible structure of the spacecraft. The schematic diagram of the coupling control method is as follows: image 3 shown. The coupling control system is mainly composed of two subsystems: attitude control compensation subsystem and vibration control compensation subsystem. The attitude control compensation subsystem mainly includes three parts: attitude sensor, attitude controller a...

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Abstract

The invention proposes a coupling control method of attitude and structural vibration of a flexible spacecraft. Including the following steps: S1, design the vibration active control method of the flexible structure, introduce the positive position feedback control algorithm into the vibration control equation, and form the spacecraft rigid-flexible coupling dynamic model including vibration control; S2, design the attitude control of the spacecraft Method, the attitude control strategy is designed based on the robust control method, and the influence of the positive position feedback control parameters is considered when designing the robust control algorithm, so as to ensure the stability of the entire coupled control system. The invention simultaneously realizes the control of the attitude of the spacecraft and the vibration of the flexible structure, improves the pointing stability of the spacecraft, and contributes to the implementation of high-precision earth observation tasks.

Description

technical field [0001] The invention relates to the research field of spacecraft dynamics and control, and specifically designs a coupling control method for flexible spacecraft attitude and structural vibration. Background technique [0002] In recent years, under the strong promotion of science and technology and the urgent traction of demand, some large spacecraft have developed in the direction of flexibility. At the same time, the goal of spacecraft attitude control has shown a development trend of high precision and high stability. The elastic vibration of the flexible structure brings severe challenges to the design of the attitude control system of the spacecraft. Therefore, it is of great significance to propose a coupling control method for spacecraft attitude and structural vibration. [0003] Generally speaking, for most flexible spacecraft, the control frequency bands between the two loops of the attitude control subsystem and the vibration control subsystem do...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05B13/04
Inventor 王杰李东旭吴军
Owner NAT UNIV OF DEFENSE TECH
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