Spacecraft attitude control by combination of various torquers

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This article addresses designing an implementable control law for spacecraft attitude manoeuvre using a combination of torque generating devices such as reaction wheels (RWs), magnetic torquers (MTs) and control moment gyros (CMGs). A compact equation of motion of a spacecraft installed with the torquers is derived. The singularity problem of CMGs is investigated by using a simple and practical virtual actuator methodology proposed in this article. A mixed control law is established for fine attitude control of an agile spacecraft manoeuvre. The control law allocates control torque to CMGs and RWs adequately to satisfy the control purpose. In the control torque allocation, the saturation problem of RWs is also addressed. Furthermore, a strategy for momentum restoration of CMGs by MTs to avoid singularity is suggested.
Publisher
TAYLOR FRANCIS LTD
Issue Date
2009
Language
English
Article Type
Article
Keywords

CONTROL-MOMENT GYROS; SINGULARITY AVOIDANCE; QUATERNION FEEDBACK; LAW

Citation

INTERNATIONAL JOURNAL OF SYSTEMS SCIENCE, v.40, no.10, pp.995 - 1008

ISSN
0020-7721
DOI
10.1080/00207720902974587
URI
http://hdl.handle.net/10203/95257
Appears in Collection
AE-Journal Papers(저널논문)
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