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Controllability of spacecraft attitude using control moment gyroscopes

DSpace at IIT Bombay

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Title Controllability of spacecraft attitude using control moment gyroscopes
 
Creator BHAT, SP
TIWARI, PAWAN K
 
Subject angular momentum
controllability
gyroscopes
nonlinear control system
 
Description This paper describes an application of nonlinear controllability theory to the problem of spacecraft attitude control using control moment gyroscopes (CMGs). Nonlinear controllability theory is used to show that a spacecraft carrying one or more CMGs is controllable on every angular momentum level set in spite of the presence of singular CMG configurations, that is, given any two states having the same angular momentum, any one of them can be reached from the other using suitably chosen motions of the CMG gimbals. This result is used to obtain sufficient conditions on the momentum volume of the CMG array that guarantee the existence of gimbal motions which steer the spacecraft to a desired spin state or rest attitude.
 
Publisher IEEE
 
Date 2009-02-21T11:34:40Z
2011-11-28T07:36:03Z
2011-12-15T09:57:08Z
2009-02-21T11:34:40Z
2011-11-28T07:36:03Z
2011-12-15T09:57:08Z
2006
 
Type Article
 
Identifier Proceedings of the 2006 American Control Conference, Minneapolis, Minnesota, USA, 14-16 June 2006, 3624-3628
1-4244-0210-7
10.1109/ACC.2006.1657281
http://hdl.handle.net/10054/744
http://dspace.library.iitb.ac.in/xmlui/handle/10054/744
 
Language en