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dc.contributor.authorAgrawal, Brij N.
dc.contributor.authorGran, Richard
dc.date.accessioned2013-09-18T18:06:04Z
dc.date.available2013-09-18T18:06:04Z
dc.date.issued1991
dc.identifier.urihttp://hdl.handle.net/10945/36463
dc.descriptionThe article of record as published may be located at http://dx.doi.org/10.2514/6.1991-2651en_US
dc.description.abstractThis paper investigates alternate control techniques for the attitude control of a three axis stabilized flexible communications satellite consisting of a large reflector and a solar array. The control configurations consisted of three classes: Class 1 - sensors and actuators co-located on the central body, Class 2 - actuator on the central body and sensors distributed, and Class 3 -actuators and sensors distributed. Criteria are developed for modal truncation. The results indicate that Class 2 can cause instability and. is not generally a desirable design approach. An experimental setup to study the effects of flexibility on attitude control per-formance during slew maneuvers and wheel desaturation is also discussed.en_US
dc.publisherMonterey, California. Naval Postgraduate Schoolen_US
dc.rightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. As such, it is in the public domain, and under the provisions of Title 17, United States Code, Section 105, may not be copyrighted.en_US
dc.titleAttitude control of flexible communications satellitesen_US


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