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dc.contributor.advisorSakoda, Daniel J.
dc.contributor.advisorHorning, James A.
dc.contributor.authorHartmann, David R.
dc.dateMar-16
dc.date.accessioned2016-04-29T21:19:29Z
dc.date.available2016-04-29T21:19:29Z
dc.date.issued2016-03
dc.identifier.urihttp://hdl.handle.net/10945/48532
dc.descriptionApproved for public release; distribution is unlimiteden_US
dc.descriptionIncludes supplementary materialen_US
dc.description.abstractThe thesis investigates the feasibility of duty cycling the GPS receiver onboard small satellites like NPSAT1 in order to repurpose power savings in ways that would better serve the satellite’s mission. Orbital propagation software run on onboard computer hardware produces accurate ephemeris data over short periods without continued GPS input. Longer periods relying on propagator ephemeris translate to greater power savings, but it also means increasing positional error. In order to better define the trade space between time and error of common propagators, Systems Tool Kit software was used to test the accuracy of the Two-Body and Simplified General Perturbations-4 propagators over time against positions measured by the Joint Space Operations Center. Two-Body propagators’ error response varies as a function of altitude and inclination, with the worst case requiring GPS updates up to twice an orbit. Simplified General Perturbations-4 propagators’ error depends strongly on the accuracy of the B* drag term, but is still sufficiently accurate to operate a day or more without a GPS update. Savings in the GPS power budget were found to exceed 96% and 99% for Two-Body and Simplified General Perturbations-4 propagators, respectively, and should be considered for use in future satellites.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 Statesen_US
dc.titlePower savings through onboard orbit propagation for small satellites like NPSAT1en_US
dc.typeThesisen_US
dc.contributor.departmentSpace Systems Academic Group
dc.contributor.departmentSpace Systems Academic Groupen_US
dc.subject.authorNPSAT1en_US
dc.subject.authorsatelliteen_US
dc.subject.authororbit propagationen_US
dc.description.serviceLieutenant, United States Navyen_US
etd.thesisdegree.nameMaster of Science in Space Systems Operationsen_US
etd.thesisdegree.levelMastersen_US
etd.thesisdegree.disciplineSpace Systems Operationsen_US
etd.thesisdegree.grantorNaval Postgraduate Schoolen_US


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