Control Moment Gyroscope Singularity Reduction via Decoupled Control

被引：0
|
作者：
Sands, Timothy A. [1 ]
Kim, Jae Jun [2 ]
Agrawal, Brij [2 ]
机构：
[1] Univ Wisconsin Madison, 663 Nautilus Court 104, Ft Walton Beach, FL 32548 USA
[2] US Navy, Postgrad Sch, Monterey, CA 93943 USA
来源：
PROCEEDINGS OF THE IEEE SOUTHEASTCON 2009, TECHNICAL PROCEEDINGS | 2009年
关键词：
D O I：
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中图分类号：
T [工业技术];
学科分类号：
08 ;
摘要：
Two objectives dominate consideration of control moment gyroscopes (CMGs) for spacecraft maneuvers: High torque (or equivalently momentum) and singularity-free operations. Utilizing a 3/4 CMG skewed-pyramid in the optimal singularity-free configuration, this paper develops a decoupled control strategy to reduce the remaining singular conditions. Analysis is provided to justify the argument with promising simulations followed by experimental verification using a free-floating satellite simulator.
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页码：388 / +
页数：2
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