Rotation matrix-based finite-time attitude coordinated control for spacecraft

Chao Tan; Guodong Xu; Limin Dong; Yaen Xie; Yushan He; Yong Hao; Fei Han

doi:10.1016/j.asr.2021.10.010

Rotation matrix-based finite-time attitude coordinated control for spacecraft

Chao Tan
, Guodong Xu
, Limin Dong^*
, Yaen Xie
, Yushan He
, Yong Hao
, Fei Han

^*Corresponding author for this work

School of Astronautics, Harbin Institute of Technology
Harbin Engineering University
Shanghai Aerospace Control Technology Institute

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

12 Scopus citations

Abstract

This paper concerns the problem of robust finite-time coordinated tracking control for spacecraft formation flying (SFF) exposed to external disturbances. An attitude controller is synthesized by the utilization of terminal sliding mode (TSM) technology and adaptive laws, where a novel sliding mode surface (SMS) has been developed for ensuring finite-time convergence. In the proposed method, rotation matrix is exploited to describe the attitude of SFF for the purpose of avoiding singularity and unwinding phenomenon. Compared with the existing methods focusing on the unwinding phenomenon, finite-time convergence is obtained for entire SFF system. The effectiveness and validity of the proposed method will be elaborated via theoretical analysis and numerical simulations.

Original language	English
Pages (from-to)	976-988
Number of pages	13
Journal	Advances in Space Research
Volume	69
Issue number	2
DOIs	https://doi.org/10.1016/j.asr.2021.10.010
State	Published - 15 Jan 2022
Externally published	Yes

Keywords

Finite-time coordinate control
Rotation matrix
Spacecraft formation flying
Terminal sliding mode

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10.1016/j.asr.2021.10.010

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title = "Rotation matrix-based finite-time attitude coordinated control for spacecraft",

abstract = "This paper concerns the problem of robust finite-time coordinated tracking control for spacecraft formation flying (SFF) exposed to external disturbances. An attitude controller is synthesized by the utilization of terminal sliding mode (TSM) technology and adaptive laws, where a novel sliding mode surface (SMS) has been developed for ensuring finite-time convergence. In the proposed method, rotation matrix is exploited to describe the attitude of SFF for the purpose of avoiding singularity and unwinding phenomenon. Compared with the existing methods focusing on the unwinding phenomenon, finite-time convergence is obtained for entire SFF system. The effectiveness and validity of the proposed method will be elaborated via theoretical analysis and numerical simulations.",

keywords = "Finite-time coordinate control, Rotation matrix, Spacecraft formation flying, Terminal sliding mode",

author = "Chao Tan and Guodong Xu and Limin Dong and Yaen Xie and Yushan He and Yong Hao and Fei Han",

note = "Publisher Copyright: {\textcopyright} 2021 COSPAR",

year = "2022",

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doi = "10.1016/j.asr.2021.10.010",

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TY - JOUR

T1 - Rotation matrix-based finite-time attitude coordinated control for spacecraft

AU - Tan, Chao

AU - Xu, Guodong

AU - Dong, Limin

AU - Xie, Yaen

AU - He, Yushan

AU - Hao, Yong

AU - Han, Fei

PY - 2022/1/15

Y1 - 2022/1/15

N2 - This paper concerns the problem of robust finite-time coordinated tracking control for spacecraft formation flying (SFF) exposed to external disturbances. An attitude controller is synthesized by the utilization of terminal sliding mode (TSM) technology and adaptive laws, where a novel sliding mode surface (SMS) has been developed for ensuring finite-time convergence. In the proposed method, rotation matrix is exploited to describe the attitude of SFF for the purpose of avoiding singularity and unwinding phenomenon. Compared with the existing methods focusing on the unwinding phenomenon, finite-time convergence is obtained for entire SFF system. The effectiveness and validity of the proposed method will be elaborated via theoretical analysis and numerical simulations.

AB - This paper concerns the problem of robust finite-time coordinated tracking control for spacecraft formation flying (SFF) exposed to external disturbances. An attitude controller is synthesized by the utilization of terminal sliding mode (TSM) technology and adaptive laws, where a novel sliding mode surface (SMS) has been developed for ensuring finite-time convergence. In the proposed method, rotation matrix is exploited to describe the attitude of SFF for the purpose of avoiding singularity and unwinding phenomenon. Compared with the existing methods focusing on the unwinding phenomenon, finite-time convergence is obtained for entire SFF system. The effectiveness and validity of the proposed method will be elaborated via theoretical analysis and numerical simulations.

KW - Finite-time coordinate control

KW - Rotation matrix

KW - Spacecraft formation flying

KW - Terminal sliding mode

UR - https://www.scopus.com/pages/publications/85118353256

U2 - 10.1016/j.asr.2021.10.010

DO - 10.1016/j.asr.2021.10.010

M3 - 文章

AN - SCOPUS:85118353256

SN - 0273-1177

VL - 69

SP - 976

EP - 988

JO - Advances in Space Research

JF - Advances in Space Research

IS - 2

ER -

Rotation matrix-based finite-time attitude coordinated control for spacecraft

Abstract

Keywords

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