Sliding mode control for a satellite attitude tracking system

Dai Gao; Jianting Lv

doi:10.1109/ISSCAA.2008.4776301

Sliding mode control for a satellite attitude tracking system

Dai Gao^*
, Jianting Lv

^*Corresponding author for this work

School of Astronautics, Harbin Institute of Technology
Heilongjiang University

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

4 Scopus citations

Abstract

The main problem addressed is the attitude tracking control of rigid satellite in the presence of inertia matrix uncertainty and external disturbances. A sliding mode controller with PID sliding surface is presented. A detail stability analysis of the close loop system is include, and while there exists uncertainty in satellite inertia parameters or external disturbance, this control scheme has global stability and robustness. Simulations are performed for the satellite attitude control system. Simulation results demonstrate that the control scheme realizes the attitude tracking control and is robust to parametric uncertainty and to external disturbance torques.

Original language	English
DOIs	https://doi.org/10.1109/ISSCAA.2008.4776301
State	Published - 2008
Externally published	Yes
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.2008.4776301

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title = "Sliding mode control for a satellite attitude tracking system",

abstract = "The main problem addressed is the attitude tracking control of rigid satellite in the presence of inertia matrix uncertainty and external disturbances. A sliding mode controller with PID sliding surface is presented. A detail stability analysis of the close loop system is include, and while there exists uncertainty in satellite inertia parameters or external disturbance, this control scheme has global stability and robustness. Simulations are performed for the satellite attitude control system. Simulation results demonstrate that the control scheme realizes the attitude tracking control and is robust to parametric uncertainty and to external disturbance torques.",

author = "Dai Gao and Jianting Lv",

year = "2008",

doi = "10.1109/ISSCAA.2008.4776301",

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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TY - CONF

T1 - Sliding mode control for a satellite attitude tracking system

AU - Gao, Dai

AU - Lv, Jianting

PY - 2008

Y1 - 2008

N2 - The main problem addressed is the attitude tracking control of rigid satellite in the presence of inertia matrix uncertainty and external disturbances. A sliding mode controller with PID sliding surface is presented. A detail stability analysis of the close loop system is include, and while there exists uncertainty in satellite inertia parameters or external disturbance, this control scheme has global stability and robustness. Simulations are performed for the satellite attitude control system. Simulation results demonstrate that the control scheme realizes the attitude tracking control and is robust to parametric uncertainty and to external disturbance torques.

AB - The main problem addressed is the attitude tracking control of rigid satellite in the presence of inertia matrix uncertainty and external disturbances. A sliding mode controller with PID sliding surface is presented. A detail stability analysis of the close loop system is include, and while there exists uncertainty in satellite inertia parameters or external disturbance, this control scheme has global stability and robustness. Simulations are performed for the satellite attitude control system. Simulation results demonstrate that the control scheme realizes the attitude tracking control and is robust to parametric uncertainty and to external disturbance torques.

UR - https://www.scopus.com/pages/publications/66449134180

U2 - 10.1109/ISSCAA.2008.4776301

DO - 10.1109/ISSCAA.2008.4776301

M3 - 论文

AN - SCOPUS:66449134180

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

Y2 - 10 December 2008 through 12 December 2008

ER -

Sliding mode control for a satellite attitude tracking system

Abstract

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