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dc.contributor.advisorLightsey, E. Glenn
dc.creatorMcDonald, Karl Josephen
dc.date.accessioned2015-02-02T20:45:45Zen
dc.date.issued2014-12en
dc.date.submittedDecember 2014en
dc.identifier.urihttp://hdl.handle.net/2152/28244en
dc.descriptiontexten
dc.description.abstractA control system is designed and validated for a 3-unit CubeSat science mission. Utilizing three magnetorquers and one reaction wheel the system achieves a 6 rotation per minute spin rate and orbit normal pointing vector of the long axis of a 3-unit CubeSat. The design is validated across an evolution of scenarios, from idealized to flight-like with expected bias and noise terms added in. Estimated mass imbalances and the limitations of the power system driving the magnetorquers force the final system design to use only magnetorquers. Considerations are also taken for the science instrument to limit the interference of magnetorquers. The overall satellite design and software implementation are also briefly discussed.en
dc.format.mimetypeapplication/pdfen
dc.language.isoenen
dc.subjectCubeSaten
dc.subjectMagneticen
dc.subjectControlen
dc.subjectSpin stabilizeden
dc.titleMagnetic control for spinning 3-unit science CubeSaten
dc.typeThesisen
dc.date.updated2015-02-02T20:45:45Zen
dc.description.departmentAerospace Engineeringen
thesis.degree.departmentAerospace Engineeringen
thesis.degree.disciplineAerospace Engineeringen
thesis.degree.grantorThe University of Texas at Austinen
thesis.degree.levelMastersen
thesis.degree.nameMaster of Science in Engineeringen


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