Acceleration feedback vibration control method for flexible structure of spacecraft

A flexible structure and acceleration technology, applied in mechanical oscillation control, non-electric variable control, control/regulation systems, etc., to avoid measurement noise and improve vibration control capabilities

Active Publication Date: 2021-12-28
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

[0006] In view of this, the present invention provides an acceleration feedback vibration control method for the flexible structure of the spacecraft, which overcomes the high-frequency overflow of the control system, and solves the problem of control effect decline caused by time lag in the closed-loop control system, and improves the vibration of the system. control ability

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  • Acceleration feedback vibration control method for flexible structure of spacecraft
  • Acceleration feedback vibration control method for flexible structure of spacecraft
  • Acceleration feedback vibration control method for flexible structure of spacecraft

Examples

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Embodiment 3

[0110] Apply the steps of Example 1 to verify the effectiveness and beneficial effects of the proposed method of the present invention. The vibration control of a certain truss scale test piece is used as a specific example for illustration. The root of the truss scale test piece is fixed and the end is free. , carry out zero-gravity unloading by means of air flotation or suspension, such as Figure 5 shown. The piezoelectric stack actuator installed at the root is used as the control output, and the acceleration sensor installed at the end is used as the control input. The structural parameters of the truss scaled test piece are as follows

[0111] Table 1 Structural parameters of truss scaled test piece

[0112] parameter value total length l 9m total mass m about 15kg base frequency 0.69Hz Modal damping ratio about 0.03

[0113] S1: According to the structural test, the dynamic parameters of the truss scaled test piece are obtain...

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Abstract

The invention discloses an acceleration feedback vibration control method for a flexible structure of a spacecraft. The method comprises the steps of obtaining a kinetic equation and a transfer function of the structure according to simulation modeling analysis or a structure test, then designing a controller based on acceleration feedback, introducing a second-order system compensator and a first-order system compensator, and configuring a damping parameter zetaf and a frequency parameter omegaf of the compensators, and finally, configuring feedback gains alpha and beta of the controller, and controlling output to add variables of the two compensators and perform negative feedback. Acceleration is used as a feedback physical quantity, so that error accumulation is avoided; a second-order system compensator is introduced, compensator variables are directly used as negative feedback, and the problem of high-frequency control overflow is solved through the low-pass filtering characteristic of the second-order system compensator; a first-order system compensator is added, and by configuring gain parameters of the two compensators, the problem that the control effect of a closed-loop control system is reduced due to time lag is solved, and the vibration control capability of the system is improved.

Description

technical field [0001] The invention relates to the technical field of vibration control, and specifically designs an acceleration feedback vibration control method suitable for flexible structures of spacecraft. Background technique [0002] With the continuous development of aerospace technology, super-large-scale, multi-functional spacecraft is an important direction for the development of spacecraft structure technology in the future. As the size gradually increases, the structure of the spacecraft presents the characteristics of large flexibility, low frequency and small damping. Due to the influence of the space environment, low-frequency vibrations are prone to occur, and once it occurs, it will attenuate slowly, affecting the high-precision and high-stability performance of the spacecraft, and may even The normal operation of the spacecraft is endangered, so the vibration control of the flexible structure of the spacecraft is of great significance. [0003] At prese...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D19/02
CPCG05D19/02
Inventor 王晓宇王祥曾福明王磊刘绍奎王慧李冰岩柴洪友
Owner BEIJING INST OF SPACECRAFT SYST ENG
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