Spacecraft attitude control based on fuzzy variable structure

Qing Wang; Ying Hua; Chao Yang Dong; Ming Lian Zhang

Spacecraft attitude control based on fuzzy variable structure

Qing Wang^*
, Ying Hua
, Chao Yang Dong
, Ming Lian Zhang

^*Corresponding author for this work

Beihang University
Beijing Aerospace Flight Control Center

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

6 Scopus citations

Abstract

The spacecraft attitude system is a nonlinear and strongly coupled system with multi-input and multi output. Basing on the nonlinear and uncertain model of the spacecraft attitude system, a fuzzy variable structure control method is proposed. The fuzzy system is used to approximate the system uncertain function. Furthermore, the errors from fuzzy approximation and external disturbances are compensated so that the influence on the system is minimized. Theoretical analysis and simulation results show that the proposed control method has high tracking accuracy and low computation load and is easy for application.

Original language	English
Pages (from-to)	1181-1184
Number of pages	4
Journal	Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica
Volume	27
Issue number	6
State	Published - Nov 2006

Keywords

Adaptability
Attitude control
Fuzzy universal approximator
Variable structure control

Cite this

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title = "Spacecraft attitude control based on fuzzy variable structure",

abstract = "The spacecraft attitude system is a nonlinear and strongly coupled system with multi-input and multi output. Basing on the nonlinear and uncertain model of the spacecraft attitude system, a fuzzy variable structure control method is proposed. The fuzzy system is used to approximate the system uncertain function. Furthermore, the errors from fuzzy approximation and external disturbances are compensated so that the influence on the system is minimized. Theoretical analysis and simulation results show that the proposed control method has high tracking accuracy and low computation load and is easy for application.",

keywords = "Adaptability, Attitude control, Fuzzy universal approximator, Variable structure control",

author = "Qing Wang and Ying Hua and Dong, \{Chao Yang\} and Zhang, \{Ming Lian\}",

year = "2006",

month = nov,

language = "英语",

volume = "27",

pages = "1181--1184",

journal = "Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica",

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T1 - Spacecraft attitude control based on fuzzy variable structure

AU - Wang, Qing

AU - Hua, Ying

AU - Dong, Chao Yang

AU - Zhang, Ming Lian

PY - 2006/11

Y1 - 2006/11

N2 - The spacecraft attitude system is a nonlinear and strongly coupled system with multi-input and multi output. Basing on the nonlinear and uncertain model of the spacecraft attitude system, a fuzzy variable structure control method is proposed. The fuzzy system is used to approximate the system uncertain function. Furthermore, the errors from fuzzy approximation and external disturbances are compensated so that the influence on the system is minimized. Theoretical analysis and simulation results show that the proposed control method has high tracking accuracy and low computation load and is easy for application.

AB - The spacecraft attitude system is a nonlinear and strongly coupled system with multi-input and multi output. Basing on the nonlinear and uncertain model of the spacecraft attitude system, a fuzzy variable structure control method is proposed. The fuzzy system is used to approximate the system uncertain function. Furthermore, the errors from fuzzy approximation and external disturbances are compensated so that the influence on the system is minimized. Theoretical analysis and simulation results show that the proposed control method has high tracking accuracy and low computation load and is easy for application.

KW - Adaptability

KW - Attitude control

KW - Fuzzy universal approximator

KW - Variable structure control

UR - https://www.scopus.com/pages/publications/33846813728

M3 - 文章

AN - SCOPUS:33846813728

SN - 1000-6893

VL - 27

SP - 1181

EP - 1184

JO - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica

JF - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica

IS - 6

ER -

Spacecraft attitude control based on fuzzy variable structure

Abstract

Keywords

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