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Kalman Filter to determine orientation and attitude of microsatellite

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dc.contributor.author COCOŞ, Natalia
dc.date.accessioned 2019-07-17T13:58:14Z
dc.date.available 2019-07-17T13:58:14Z
dc.date.issued 2011
dc.identifier.citation COCOŞ, Natalia. Kalman Filter to determine orientation and attitude of microsatellite. In: Conferința Tehnico-Științifică a Colaboratorilor, Doctoranzilor și Studenților, Universitatea Tehnică a Moldovei, 17 – 19 noiembrie, 2010. Chișinău, 2011, vol. 1, pp. 82-86. ISBN 978-9975-45-065-2. ISBN 978-9975-45-158-1 (Vol.1). en_US
dc.identifier.isbn 978-9975-45-065-2
dc.identifier.uri http://repository.utm.md/handle/5014/3626
dc.description.abstract The nonlinear problem of tracking and predicting where a satellite will be over some time can be difficult with the recognition of modeling error and ground site radar tracking errors. For this reason it is important to have an accurate modeling program with the fidelity to correct for any errors in orbital motion and predict the most accurate positioning at some future time. The Extended Kalman Filter is one such program that can accurately determine position over time given estimate ranges for sources of error. However, the Extended Kalman Filter contains many linear approximations that allow its prediction and correction methods to work. This paper will discuss the effects of replacing the linearizing approaches made in the orbital model part of the program with numerical small-step approaches. en_US
dc.language.iso en en_US
dc.publisher Tehnica UTM en_US
dc.rights Attribution-NonCommercial-NoDerivs 3.0 United States *
dc.rights.uri http://creativecommons.org/licenses/by-nc-nd/3.0/us/ *
dc.subject Kalman Filter en_US
dc.subject en_US
dc.subject en_US
dc.subject en_US
dc.subject microsatellites en_US
dc.subject satellites en_US
dc.title Kalman Filter to determine orientation and attitude of microsatellite en_US
dc.type Article en_US


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