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dc.contributor.advisorLarsen, Bjørn B.nb_NO
dc.contributor.advisorBirkeland, Roger
dc.contributor.authorKiær, Christian Eliasnb_NO
dc.contributor.authorArnesen, Magnus Haglund
dc.date.accessioned2014-12-19T13:50:07Z
dc.date.accessioned2015-12-22T11:50:56Z
dc.date.available2014-12-19T13:50:07Z
dc.date.available2015-12-22T11:50:56Z
dc.date.created2014-09-17nb_NO
dc.date.issued2014nb_NO
dc.identifier747981nb_NO
dc.identifierntnudaim:11069
dc.identifier.urihttp://hdl.handle.net/11250/2371107
dc.description.abstractNTNU Test Satellite (NUTS) is a student-built double CubeSat with a scheduled launch in 2015. The project is multidisciplinary where students from all specialities can apply both for thesis assignments and volunteer work. The satellite will be in a low earth orbit (LEO) where radiation creates a challenging environment for electronics and on-board systems. To counter the effects of space radiation, a thorough and detailed mission event plan, as well as battery estimation and methods for removing lasting faults have been evaluated and implemented.Two watchdog solutions have been suggested, a global watchdog with triple modular redundancy (TMR) on the backplane and a solution with a local watchdog on each master module. Both solutions have the capability to remove single event latchups (SEL) by temporarily removing power to the affected module. Based on results and analysis, the solution with two local watchdogs are the preferred solution due to the increased complexity of the TMR solution. Furthermore, the voter necessary in a TMR implementation is a single point of failure which if malfunctioning, will leave the satellite unresponsive. Guidelines for choosing a new watchdog system's parameters are given. This includes the watchdog's time-out period, power-on-reset (POR) delay and a threshold voltage for the voltage supervisory function.Mission event plans are proposed for initial power-up, in-orbit power monitoring, payload verification and satellite self-tests. A flowchart defining a software watchdog responsible for maintaining an operational satellite is also presented.An adjustable beacon rate enables power conservation by defining three different transmission rates; low, normal and full rate. For the full rate, the power consumption is estimated to 2200 mW, 233.33 % higher than in low rate and 100 % higher than normal rate. A battery management framework has been proposed in order to avoid a low battery condition.nb_NO
dc.languageengnb_NO
dc.publisherInstitutt for elektronikk og telekommunikasjonnb_NO
dc.titleMission Event Planning & Error-Recovery for CubeSat Applicationsnb_NO
dc.typeMaster thesisnb_NO
dc.source.pagenumber132nb_NO
dc.contributor.departmentNorges teknisk-naturvitenskapelige universitet, Fakultet for informasjonsteknologi, matematikk og elektroteknikk, Institutt for elektronikk og telekommunikasjonnb_NO


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