NDLI: A micro-satellite attitude system using sliding mode observer and sliding mode controller with perturbation estimation

Content Provider	IEEE Xplore Digital Library
Author	Yuehua Cheng Bin Jiang Xian Zhang
Copyright Year	2008
Description	Author affiliation: Coll. of Autom. Eng., Nanjing Univ. of Aeronaut. & Astronaut., Nanjing (Bin Jiang; Xian Zhang) \|\| Acad. of Frontier Sci., Nanjing Univ. of Aeronaut. & Astronaut., Nanjing (Yuehua Cheng)
Abstract	In this paper, we present sliding mode observer (SMO) and sliding mode controller with perturbation estimation (SMCPE) for a micro-satellite attitude system. In view of the microsatellite attitude system where gyro is not available or gyro fails, the quaternion estimating angle rate of satellite is proposed by means of sliding mode observer. The SMO is suitable for microsatellite which is limit by weight and power. SMCPE is applied to achieve tracking with good accuracy and enhance the robustness of the system. The simulation results about a spacecraft example show the efficiency and advantages of the proposed SMCPE method.
Starting Page	1
Ending Page	4
File Size	1434799
Page Count	4
File Format	PDF
ISBN	9781424439089
DOI	10.1109/ISSCAA.2008.4776305
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2008-12-10
Publisher Place	China
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Space vehicles Satellites Attitude control Quaternions Linearization techniques Position measurement Control systems Educational institutions Robustness Sliding mode control
Content Type	Text
Resource Type	Article

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