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INS/GPS Integration Using Parallel Kalman Filtering

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dc.contributor.authorHajiyev, Chingiz
dc.contributor.authorAykut Tutucu, M.
dc.date.accessioned2026-01-25T05:36:31Z
dc.date.issued2001-09-01
dc.description.abstractAbstract In the paper an algorithm on aiding the Inertial Navigation System with GPS is presented. Parallel Kalman filter, which includes two different Kalman filters and processes INS and GPS data in real time, is designed for this reason. Simulation is made and presented on flight dynamics, and it is determined that the algorithm for aiding the INS with GPS, evaluates the motion parameters with high accuracy.
dc.description.urihttps://doi.org/10.1016/s1474-6670(17)40778-6
dc.description.urihttps://dx.doi.org/10.1016/s1474-6670(17)40778-6
dc.identifier.doi10.1016/s1474-6670(17)40778-6
dc.identifier.endpage517
dc.identifier.issn1474-6670
dc.identifier.openairedoi_dedup___::6e3135663c555f7b181ac2e6dd4c0d2b
dc.identifier.orcid0000-0003-4115-341x
dc.identifier.startpage512
dc.identifier.urihttps://hdl.handle.net/11527/47160
dc.identifier.volume34
dc.language.isoeng
dc.publisherElsevier BV
dc.relation.ispartofIFAC Proceedings Volumes
dc.rightsCLOSED
dc.titleINS/GPS Integration Using Parallel Kalman Filtering
dc.typeArticle
dspace.entity.typePublication

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