基于动态滑模控制的挠性航天器姿态控制

Qing Hua Zhu; Rui Qi Dong; Guang Fu Ma

doi:10.7641/CTA.2018.70863

基于动态滑模控制的挠性航天器姿态控制

Translated title of the contribution: Dynamical sliding mode for flexible spacecraft attitude control

Qing Hua Zhu
, Rui Qi Dong^*
, Guang Fu Ma

^*Corresponding author for this work

School of Astronautics

Harbin Institute of Technology
Shanghai Aerospace Control Technology Institute
Shanghai Key Laboratory of Aerospace Intelligence Control Technology
Harbin Institute of Technology Shenzhen

Research output: Contribution to journal › Article › peer-review

9 Scopus citations

Abstract

In this paper, the sliding mode control technique is adopted to design attitude stable controllers for flexible spacecraft. First, the mathematical model of the flexible spacecraft is constructed. The kinematic equation of the flexible spacecraft is described by quaternion. Then, by introducing the dynamical switching function, an dynamical sliding mode control law is proposed for the flexible spacecraft attitude control. The proposed dynamical sliding mode control law can suppress the chattering raised by the sign function of the control law. Finally, a numerical example is employed to verify the effectiveness of the presented control law.

Translated title of the contribution	Dynamical sliding mode for flexible spacecraft attitude control
Original language	Chinese (Traditional)
Pages (from-to)	1430-1435
Number of pages	6
Journal	Kongzhi Lilun Yu Yingyong/Control Theory and Applications
Volume	35
Issue number	10
DOIs	https://doi.org/10.7641/CTA.2018.70863
State	Published - 1 Oct 2018

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title = "基于动态滑模控制的挠性航天器姿态控制",

abstract = "In this paper, the sliding mode control technique is adopted to design attitude stable controllers for flexible spacecraft. First, the mathematical model of the flexible spacecraft is constructed. The kinematic equation of the flexible spacecraft is described by quaternion. Then, by introducing the dynamical switching function, an dynamical sliding mode control law is proposed for the flexible spacecraft attitude control. The proposed dynamical sliding mode control law can suppress the chattering raised by the sign function of the control law. Finally, a numerical example is employed to verify the effectiveness of the presented control law.",

keywords = "Attitude stabilization, Dynamical sliding mode control, Flexible spacecraft",

author = "Zhu, \{Qing Hua\} and Dong, \{Rui Qi\} and Ma, \{Guang Fu\}",

year = "2018",

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doi = "10.7641/CTA.2018.70863",

language = "繁体中文",

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T1 - 基于动态滑模控制的挠性航天器姿态控制

AU - Zhu, Qing Hua

AU - Dong, Rui Qi

AU - Ma, Guang Fu

PY - 2018/10/1

Y1 - 2018/10/1

N2 - In this paper, the sliding mode control technique is adopted to design attitude stable controllers for flexible spacecraft. First, the mathematical model of the flexible spacecraft is constructed. The kinematic equation of the flexible spacecraft is described by quaternion. Then, by introducing the dynamical switching function, an dynamical sliding mode control law is proposed for the flexible spacecraft attitude control. The proposed dynamical sliding mode control law can suppress the chattering raised by the sign function of the control law. Finally, a numerical example is employed to verify the effectiveness of the presented control law.

AB - In this paper, the sliding mode control technique is adopted to design attitude stable controllers for flexible spacecraft. First, the mathematical model of the flexible spacecraft is constructed. The kinematic equation of the flexible spacecraft is described by quaternion. Then, by introducing the dynamical switching function, an dynamical sliding mode control law is proposed for the flexible spacecraft attitude control. The proposed dynamical sliding mode control law can suppress the chattering raised by the sign function of the control law. Finally, a numerical example is employed to verify the effectiveness of the presented control law.

KW - Attitude stabilization

KW - Dynamical sliding mode control

KW - Flexible spacecraft

UR - https://www.scopus.com/pages/publications/85059435862

U2 - 10.7641/CTA.2018.70863

DO - 10.7641/CTA.2018.70863

M3 - 文章

AN - SCOPUS:85059435862

SN - 1000-8152

VL - 35

SP - 1430

EP - 1435

JO - Kongzhi Lilun Yu Yingyong/Control Theory and Applications

JF - Kongzhi Lilun Yu Yingyong/Control Theory and Applications

IS - 10

ER -

基于动态滑模控制的挠性航天器姿态控制

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