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dc.contributor.advisorAgrawal, Brij N.
dc.contributor.authorKulick, Wayne J.
dc.date.accessioned2012-03-14T17:30:59Z
dc.date.available2012-03-14T17:30:59Z
dc.date.issued2004-12
dc.identifier.urihttp://hdl.handle.net/10945/1229
dc.description.abstractThis thesis develops and implements a Control Moment Gyroscope (CMG) steering law, controller and active balancing system for a three-axis satellite simulator (TASS). The CMGs are configured in a typical pyramid configuration (the fourth CMG position being null). The development was done primarily with simulation and experiments utilizing Real Time Workshop and XPC Target of MATLAB and SIMULINK. The TASS is a double circular platform mounted on a spherical air bearing with the center of rotation (CR) about the approximate physical geometric center of the simulator. The TASS utilizes three moveable masses in the three body axes for balancing which actively eliminate any center of gravity (CG) offset and return the CG to the CR. The TASS supports an optics payload designed to acquire, track and point a received laser beam onto an off-satellite target. The target may be stationary or moving. Actively balancing the TASS reduces the torque output requirement for the CMGs while maintaining either a stabilized level platform or a particular commanded attitude. Reduction or elimination of torque output from the CMGs results in a more stabilized platform, less structural induced vibration, less jitter in payload optics and less power required in spacecraft applications.en_US
dc.description.urihttp://archive.org/details/developmentofcon109451229
dc.format.extentxviii, 105 p. : ill. (some col.) ;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. Copyright protection is not available for this work in the United States.en_US
dc.subject.lcshArtificial satellitesen_US
dc.subject.lcshRotationen_US
dc.subject.lcshAttitudeen_US
dc.subject.lcshGyroscopic instrumentsen_US
dc.subject.lcshAstronautical instrumentsen_US
dc.titleDevelopment of a Control Moment Gyroscope controlled, three axis satellite simulator, with active balancing for the bifocal relay mirror initiativeen_US
dc.typeThesisen_US
dc.contributor.secondreaderKim, Jong-Woo
dc.contributor.corporateNaval Postgraduate School (U.S.).
dc.contributor.departmentMechanical and Astronautical Engineering
dc.subject.authorSatellite Simulatoren_US
dc.subject.authorActive Balancingen_US
dc.subject.authorAuto Balancingen_US
dc.subject.authorControl Moment Gyroscopeen_US
dc.subject.authorCMGen_US
dc.subject.authorAir Bearingen_US
dc.description.serviceLieutenant Commander, United States Navyen_US
etd.thesisdegree.nameM.S. in Astronautical Engineeringen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineAstronautical Engineeringen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US
dc.description.distributionstatementApproved for public release; distribution is unlimited.


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