Design and robust analysis for spacecraft attitude controller

Zhou Fengqi; Han Yanhua; Zhou Jun

Design and robust analysis for spacecraft attitude controller

Zhou Fengqi, Han Yanhua, Zhou Jun

School of Astronautics

Northwestern Polytechnical University Xian

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

2 Scopus citations

Abstract

The spacecraft's attitude control system was divided into the outer loop that was angle loop and the inner loop that was angle velocity loop based on their time scales. Then the control law of each loop was designed independently using exact linearization method. In the inner loop, robust stability was analysed using small-gain theorem considering the existence of perturbation of spacecraft moment inertia.

Original language	English
Pages (from-to)	36-41
Number of pages	6
Journal	Zhongguo Kongjian Kexue Jishu/Chinese Space Science and Technology
Volume	27
Issue number	2
State	Published - Apr 2007

Keywords

Exact linearization
Robust control attitude control
Singular perturbation
Small-gain theorem
Vehicle

Cite this

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title = "Design and robust analysis for spacecraft attitude controller",

abstract = "The spacecraft's attitude control system was divided into the outer loop that was angle loop and the inner loop that was angle velocity loop based on their time scales. Then the control law of each loop was designed independently using exact linearization method. In the inner loop, robust stability was analysed using small-gain theorem considering the existence of perturbation of spacecraft moment inertia.",

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author = "Zhou Fengqi and Han Yanhua and Zhou Jun",

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AU - Jun, Zhou

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AB - The spacecraft's attitude control system was divided into the outer loop that was angle loop and the inner loop that was angle velocity loop based on their time scales. Then the control law of each loop was designed independently using exact linearization method. In the inner loop, robust stability was analysed using small-gain theorem considering the existence of perturbation of spacecraft moment inertia.

KW - Exact linearization

KW - Robust control attitude control

KW - Singular perturbation

KW - Small-gain theorem

KW - Vehicle

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JF - Zhongguo Kongjian Kexue Jishu/Chinese Space Science and Technology

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Design and robust analysis for spacecraft attitude controller

Abstract

Keywords

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