Attitude control of a bias momentum satellite using moment of inertia

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Analysis on the attitude controller based upon moment of inertia distribution for a bias momentum satellite is discussed. Spacecraft moment of inertia distribution is represented in the form of product of inertia terms in the system inertia matrix. The product of inertia between orthogonal body axes of the satellite is used to build a controller which controls the notational motion caused by the angular momentum of the wheel. The attitude controller in the pitch axis controlling the pitch motion as well as nutational dynamics in the roll/yaw planes is analyzed in detail. Analytic expressions using linearized equations are derived providing further insight into the dynamic coupling effect among orthogonal body axes.
Publisher
IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC
Issue Date
2002-01
Language
English
Article Type
Article
Citation

IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS, v.38, no.1, pp.243 - 250

ISSN
0018-9251
URI
http://hdl.handle.net/10203/12167
Appears in Collection
AE-Journal Papers(저널논문)
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