Purpose Large space structures have been explored and constructed to meet the rising demand for high-resolution capabilities in remote sensing satellites. These satellites typically perform fast attitude maneuvers to achieve mission objectives, inevitably resulting in vibrations of the flexible appendages. In this paper, a network of piezoelectric active actuators is utilized to attenuate the micro-vibrations of a long three-dimensional articulated mast during attitude maneuvers. Methods First, the dynamic equations of the piezoelectric active rod are derived using the finite element method in conjunction with the Guyan reduction technique. Second, the coupled governing equations of the flexible satellite considering the piezoelectric materials are formulated. The Gramian-based technique, with higher computational efficiency than other methods, is used to determine the ideal placement of the actuators. An integrated control strategy is developed to suppress vibration during attitude maneuvers. Pitch and roll attitude maneuvers are performed to evaluate the effectiveness of the proposed control system. The direct velocity feedback control method is implemented to mitigate vibration. Results The simulation results illustrate that the tip displacement of the mast is reduced by <InlineEquation ID="IEq1"> <InlineMediaObject> <ImageObject Color="BlackWhite" FileRef="42417_2025_1841_Article_IEq1.gif" Format="GIF" Height="16" Rendition="HTML" Resolution="72" Type="Linedraw" Width="31" /> </InlineMediaObject> <EquationSource Format="TEX">$70\%$</EquationSource> <EquationSource Format="MATHML"><math> <mrow> <mn>70</mn> <mo>%</mo> </mrow> </math></EquationSource> </InlineEquation> and <InlineEquation ID="IEq2"> <InlineMediaObject> <ImageObject Color="BlackWhite" FileRef="42417_2025_1841_Article_IEq2.gif" Format="GIF" Height="16" Rendition="HTML" Resolution="72" Type="Linedraw" Width="31" /> </InlineMediaObject> <EquationSource Format="TEX">$88\%$</EquationSource> <EquationSource Format="MATHML"><math> <mrow> <mn>88</mn> <mo>%</mo> </mrow> </math></EquationSource> </InlineEquation> in 0.5 s during the pitch and roll attitude maneuvers, meeting the high-performance requirements of the satellite instrument.

Vibration Control System Design Using Active Devices for Large Space Structure During Attitude Maneuver

期刊论文
发表日期：

2025年5月12日

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Shengyu Lin,
Yang Zhao,
Wenlai Ma

摘要

Purpose

Large space structures have been explored and constructed to meet the rising demand for high-resolution capabilities in remote sensing satellites. These satellites typically perform fast attitude maneuvers to achieve mission objectives, inevitably resulting in vibrations of the flexible appendages. In this paper, a network of piezoelectric active actuators is utilized to attenuate the micro-vibrations of a long three-dimensional articulated mast during attitude maneuvers.

Methods

First, the dynamic equations of the piezoelectric active rod are derived using the finite element method in conjunction with the Guyan reduction technique. Second, the coupled governing equations of the flexible satellite considering the piezoelectric materials are formulated. The Gramian-based technique, with higher computational efficiency than other methods, is used to determine the ideal placement of the actuators. An integrated control strategy is developed to suppress vibration during attitude maneuvers. Pitch and roll attitude maneuvers are performed to evaluate the effectiveness of the proposed control system. The direct velocity feedback control method is implemented to mitigate vibration.

Results

The simulation results illustrate that the tip displacement of the mast is reduced by $70\%$ $70 %$ and $88\%$ $88 %$ in 0.5 s during the pitch and roll attitude maneuvers, meeting the high-performance requirements of the satellite instrument.