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dc.contributor.advisorSinclair, Andrewen_US
dc.contributor.authorHebert, Lauraen_US
dc.date.accessioned2016-04-29T18:46:58Z
dc.date.available2016-04-29T18:46:58Z
dc.date.issued2016-04-29
dc.identifier.urihttp://hdl.handle.net/10415/5073
dc.description.abstractFor relative-orbit determination using linear, Cartesian dynamics, angles-only measurements are not sufficient. A known, impulsive maneuver performed by either the observer or resident space object can provide observability. However, some maneuvers result in singular measurement equations and therefore do not provide full-state observability. These singular maneuvers can be avoided, but no further information can be provided about desirable maneuvers. The goal of this work is to provide an iterative method to improve observability and the accuracy of the solution. Successive maneuvers planned from covariance predictions using previous state estimates give increasingly good estimates.en_US
dc.subjectAerospace Engineeringen_US
dc.titleAngles-Only Initial Relative-Orbit Determination via Successive Maneuversen_US
dc.typeMaster's Thesisen_US
dc.embargo.statusNOT_EMBARGOEDen_US
dc.contributor.committeeLovell, T. Alanen_US
dc.contributor.committeeCicci, Daviden_US
dc.contributor.committeeCochran, Johnen_US


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