Backstepping-based attitude maneuver control and active vibration reduction of flexible spacecraft

Liangkuan Zhu; Yaqiu Liu; Dailin Wang; Qinglei Hu

doi:10.1109/CCDC.2008.4597441

Backstepping-based attitude maneuver control and active vibration reduction of flexible spacecraft

Liangkuan Zhu^*
, Yaqiu Liu
, Dailin Wang
, Qinglei Hu

^*Corresponding author for this work

Northeast Forestry University
Harbin Institute of Technology

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

4 Scopus citations

Abstract

A novel hybrid robust control design method is investigated for a three-axis-rotational maneuver and vibration stabilization of a spacecraft with flexible appendages. Based on the backstepping , a robust attitude control law is derived to control the attitude motion of spacecraft. For actively suppressing the induced vibration, strain rate feedback control methods are presented by using piezoelectric materials as additional sensors and actuators bonded on the surface of the flexible appendages. Numerical simulations demonstrate the feasibility and effectiveness of the control strategy.

Original language	English
Title of host publication	Chinese Control and Decision Conference, 2008, CCDC 2008
Pages	887-891
Number of pages	5
DOIs	https://doi.org/10.1109/CCDC.2008.4597441
State	Published - 2008
Externally published	Yes
Event	Chinese Control and Decision Conference 2008, CCDC 2008 - Yantai, Shandong, China Duration: 2 Jul 2008 → 4 Jul 2008

Publication series

Name	Chinese Control and Decision Conference, 2008, CCDC 2008

Conference

Conference	Chinese Control and Decision Conference 2008, CCDC 2008
Country/Territory	China
City	Yantai, Shandong
Period	2/07/08 → 4/07/08

Keywords

Attitude maneuvering
Backstepping
Flexible spacecraft

Access to Document

10.1109/CCDC.2008.4597441

Cite this

@inproceedings{42200c00a42a4feeb68301c217782f96,

title = "Backstepping-based attitude maneuver control and active vibration reduction of flexible spacecraft",

abstract = "A novel hybrid robust control design method is investigated for a three-axis-rotational maneuver and vibration stabilization of a spacecraft with flexible appendages. Based on the backstepping , a robust attitude control law is derived to control the attitude motion of spacecraft. For actively suppressing the induced vibration, strain rate feedback control methods are presented by using piezoelectric materials as additional sensors and actuators bonded on the surface of the flexible appendages. Numerical simulations demonstrate the feasibility and effectiveness of the control strategy.",

keywords = "Attitude maneuvering, Backstepping, Flexible spacecraft",

author = "Liangkuan Zhu and Yaqiu Liu and Dailin Wang and Qinglei Hu",

year = "2008",

doi = "10.1109/CCDC.2008.4597441",

language = "英语",

isbn = "9781424417346",

series = "Chinese Control and Decision Conference, 2008, CCDC 2008",

pages = "887--891",

booktitle = "Chinese Control and Decision Conference, 2008, CCDC 2008",

note = "Chinese Control and Decision Conference 2008, CCDC 2008 ; Conference date: 02-07-2008 Through 04-07-2008",

}

Zhu, L, Liu, Y, Wang, D & Hu, Q 2008, Backstepping-based attitude maneuver control and active vibration reduction of flexible spacecraft. in Chinese Control and Decision Conference, 2008, CCDC 2008., 4597441, Chinese Control and Decision Conference, 2008, CCDC 2008, pp. 887-891, Chinese Control and Decision Conference 2008, CCDC 2008, Yantai, Shandong, China, 2/07/08. https://doi.org/10.1109/CCDC.2008.4597441

Backstepping-based attitude maneuver control and active vibration reduction of flexible spacecraft. / Zhu, Liangkuan; Liu, Yaqiu; Wang, Dailin et al.
Chinese Control and Decision Conference, 2008, CCDC 2008. 2008. p. 887-891 4597441 (Chinese Control and Decision Conference, 2008, CCDC 2008).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

TY - GEN

T1 - Backstepping-based attitude maneuver control and active vibration reduction of flexible spacecraft

AU - Zhu, Liangkuan

AU - Liu, Yaqiu

AU - Wang, Dailin

AU - Hu, Qinglei

PY - 2008

Y1 - 2008

N2 - A novel hybrid robust control design method is investigated for a three-axis-rotational maneuver and vibration stabilization of a spacecraft with flexible appendages. Based on the backstepping , a robust attitude control law is derived to control the attitude motion of spacecraft. For actively suppressing the induced vibration, strain rate feedback control methods are presented by using piezoelectric materials as additional sensors and actuators bonded on the surface of the flexible appendages. Numerical simulations demonstrate the feasibility and effectiveness of the control strategy.

AB - A novel hybrid robust control design method is investigated for a three-axis-rotational maneuver and vibration stabilization of a spacecraft with flexible appendages. Based on the backstepping , a robust attitude control law is derived to control the attitude motion of spacecraft. For actively suppressing the induced vibration, strain rate feedback control methods are presented by using piezoelectric materials as additional sensors and actuators bonded on the surface of the flexible appendages. Numerical simulations demonstrate the feasibility and effectiveness of the control strategy.

KW - Attitude maneuvering

KW - Backstepping

KW - Flexible spacecraft

UR - https://www.scopus.com/pages/publications/52349090851

U2 - 10.1109/CCDC.2008.4597441

DO - 10.1109/CCDC.2008.4597441

M3 - 会议稿件

AN - SCOPUS:52349090851

SN - 9781424417346

T3 - Chinese Control and Decision Conference, 2008, CCDC 2008

SP - 887

EP - 891

BT - Chinese Control and Decision Conference, 2008, CCDC 2008

T2 - Chinese Control and Decision Conference 2008, CCDC 2008

Y2 - 2 July 2008 through 4 July 2008

ER -

Backstepping-based attitude maneuver control and active vibration reduction of flexible spacecraft

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Keywords

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