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dc.contributor.advisorVadali, Srinivas R.
dc.creatorFritz, Matthew Peyton
dc.date.accessioned2011-02-22T22:23:43Z
dc.date.accessioned2011-02-22T23:45:25Z
dc.date.available2011-02-22T22:23:43Z
dc.date.available2011-02-22T23:45:25Z
dc.date.created2009-12
dc.date.issued2011-02-22
dc.date.submittedDecember 2009
dc.identifier.urihttps://hdl.handle.net/1969.1/ETD-TAMU-2009-12-7338
dc.description.abstractRelative global positioning system (GPS) navigation is currently used for autonomous rendezvous and docking of two spacecraft as well as formation flying applications. GPS receivers deliver measurements to flight software that use this information to determine estimates of the current states of the spacecraft. The success of autonomous proximity operations in the presence of an uncertain environment and noisy measurements depends primarily on the navigation accuracy. This thesis presents the implementation and calibration of a spaceborne GPS receiver model, a visibility analysis for multiple GPS antenna cone angles, the implementation of four different extended Kalman filter architectures and a comparison of the advantages and disadvantages of each filter used for relative GPS navigation. A spaceborne GPS model is developed to generate simulated GPS measurements for a spacecraft located on any orbit around the Earth below the GPS constellation. Position and velocity estimation algorithms for GPS receivers are developed and implemented. A visibility analysis is performed to determine the number of visible satellites throughout the duration of the rendezvous. Multiple constant fields of view are analyzed and results compared to develop an understanding of how the GPS constellation evolves during the proximity operations. The comparison is used to choose a field of view with adequate satellite coverage. The advantages and disadvantages of the relative navigation architectures are evaluated based on a trade study involving several parameters. It is determined in this thesis that a reduced pseudorange filter provides the best overall performance in both relative and absolute navigation with less computational cost than the slightly more accurate pseudorange lter. A relative pseudorange architecture experiences complications due to multipath rich environments and performs well in only relative navigation. A position velocity architecture performs well in absolute state estimation but the worst of the four filters studied in relative state estimation.en
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.subjectGPSen
dc.subjectDevelopment of GPS sensor model for orbiting spacecraften
dc.subjectNavigationen
dc.subjectStudy of different Kalman architectures for relative GPS navigationen
dc.subjectComparisonen
dc.subjectComparison of four Kalman filters to determine advantages and disadvantages of each for relative GPS navigationen
dc.titleA Comparative Study of Kalman Filter Implementations for Relative GPS Navigationen
dc.typeThesisen
thesis.degree.departmentAerospace Engineeringen
thesis.degree.disciplineAerospace Engineeringen
thesis.degree.grantorTexas A&M Universityen
thesis.degree.nameMaster of Scienceen
thesis.degree.levelMastersen
dc.contributor.committeeMemberKalmar-Nagy, Tamas
dc.contributor.committeeMemberDatta, Aniruddha
dc.contributor.committeeMemberZanetti, Renato
dc.type.genrethesisen
dc.type.materialtexten


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