Attitude tracking control of on-orbit-servicing spacecraft based on eigenaxis maneuver

Feng Wang; Xue Qin Chen; Xi Bin Cao

doi:10.1109/ISSCAA.2008.4776272

Attitude tracking control of on-orbit-servicing spacecraft based on eigenaxis maneuver

Feng Wang^*
, Xue Qin Chen
, Xi Bin Cao

^*Corresponding author for this work

School of Astronautics

Harbin Institute of Technology

Research output: Contribution to conference › Paper › peer-review

1 Scopus citations

Abstract

An eigenaxis tracking control algorithm is present ed to provide rapid attitude tracking and synchronized rot ation for on-orbit-servicing spacecraft. Based on the relative motion error dynamic equation, the algorithm uses the s trategy similar with the move-to-rest attitude maneuver an d imports a parameter describing the deviation degree fro m eigenaxis as feedback to ensure the whole tracking is an eigenaxis rotation. Finally, It carries out the s imulation. And the results indicate the smooth maneuver process, high error accuracy, short tracking path and near optimal time are achieved after the whole tracking.

Original language	English
DOIs	https://doi.org/10.1109/ISSCAA.2008.4776272
State	Published - 2008
Event	2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics, ISSCAA 2008 - Shenzhen, China Duration: 10 Dec 2008 → 12 Dec 2008

Conference

Conference	2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics, ISSCAA 2008
Country/Territory	China
City	Shenzhen
Period	10/12/08 → 12/12/08

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10.1109/ISSCAA.2008.4776272

Cite this

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title = "Attitude tracking control of on-orbit-servicing spacecraft based on eigenaxis maneuver",

abstract = "An eigenaxis tracking control algorithm is present ed to provide rapid attitude tracking and synchronized rot ation for on-orbit-servicing spacecraft. Based on the relative motion error dynamic equation, the algorithm uses the s trategy similar with the move-to-rest attitude maneuver an d imports a parameter describing the deviation degree fro m eigenaxis as feedback to ensure the whole tracking is an eigenaxis rotation. Finally, It carries out the s imulation. And the results indicate the smooth maneuver process, high error accuracy, short tracking path and near optimal time are achieved after the whole tracking.",

author = "Feng Wang and Chen, \{Xue Qin\} and Cao, \{Xi Bin\}",

year = "2008",

doi = "10.1109/ISSCAA.2008.4776272",

language = "英语",

note = "2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics, ISSCAA 2008 ; Conference date: 10-12-2008 Through 12-12-2008",

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T1 - Attitude tracking control of on-orbit-servicing spacecraft based on eigenaxis maneuver

AU - Wang, Feng

AU - Chen, Xue Qin

AU - Cao, Xi Bin

PY - 2008

Y1 - 2008

N2 - An eigenaxis tracking control algorithm is present ed to provide rapid attitude tracking and synchronized rot ation for on-orbit-servicing spacecraft. Based on the relative motion error dynamic equation, the algorithm uses the s trategy similar with the move-to-rest attitude maneuver an d imports a parameter describing the deviation degree fro m eigenaxis as feedback to ensure the whole tracking is an eigenaxis rotation. Finally, It carries out the s imulation. And the results indicate the smooth maneuver process, high error accuracy, short tracking path and near optimal time are achieved after the whole tracking.

AB - An eigenaxis tracking control algorithm is present ed to provide rapid attitude tracking and synchronized rot ation for on-orbit-servicing spacecraft. Based on the relative motion error dynamic equation, the algorithm uses the s trategy similar with the move-to-rest attitude maneuver an d imports a parameter describing the deviation degree fro m eigenaxis as feedback to ensure the whole tracking is an eigenaxis rotation. Finally, It carries out the s imulation. And the results indicate the smooth maneuver process, high error accuracy, short tracking path and near optimal time are achieved after the whole tracking.

UR - https://www.scopus.com/pages/publications/66449084974

U2 - 10.1109/ISSCAA.2008.4776272

DO - 10.1109/ISSCAA.2008.4776272

M3 - 论文

AN - SCOPUS:66449084974

T2 - 2008 2nd International Symposium on Systems and Control in Aerospace and Astronautics, ISSCAA 2008

Y2 - 10 December 2008 through 12 December 2008

ER -

Attitude tracking control of on-orbit-servicing spacecraft based on eigenaxis maneuver

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