Please use this identifier to cite or link to this item: http://hdl.handle.net/10397/80857
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dc.contributorDepartment of Building and Real Estateen_US
dc.creatorQiao, Jen_US
dc.creatorChen, Wen_US
dc.creatorJi, Sen_US
dc.creatorWeng, Den_US
dc.date.accessioned2019-06-27T06:36:08Z-
dc.date.available2019-06-27T06:36:08Z-
dc.identifier.urihttp://hdl.handle.net/10397/80857-
dc.language.isoenen_US
dc.publisherMolecular Diversity Preservation International (MDPI)en_US
dc.rights© 2019 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (http://creativecommons.org/licenses/by/4.0/).en_US
dc.rightsThe following publication Qiao J, Chen W, Ji S, Weng D. Accurate and Rapid Broadcast Ephemerides for Beidou-Maneuvered Satellites. Remote Sensing. 2019; 11(7):787 is available at https://doi.org/10.3390/rs11070787en_US
dc.subjectBeidouen_US
dc.subjectBroadcast ephemerisen_US
dc.subjectManeuver detectionen_US
dc.subjectThrust forceen_US
dc.titleAccurate and rapid broadcast ephemerides for Beidou-maneuvered satellitesen_US
dc.typeJournal/Magazine Articleen_US
dc.identifier.volume11en_US
dc.identifier.issue7en_US
dc.identifier.doi10.3390/rs11070787en_US
dcterms.abstractThe geostationary earth orbit (GEO) and inclined geosynchronous orbit (IGSO) satellites of the Beidou navigation satellite system are maneuvered frequently. The broadcast ephemeris can be interrupted for several hours after the maneuver. The orbit-only signal-in-space ranging errors (SISREs) of broadcast ephemerides available after the interruption are over two times larger than the errors during normal periods. To shorten the interruption period and improve the ephemeris accuracy, we propose a two-step orbit recovery strategy based on a piecewise linear thrust model. The turning points of the thrust model are firstly determined by comparison of the kinematic orbit with an integrated orbit free from maneuver; afterward, precise orbit determination (POD) is conducted for the maneuvered satellite by estimating satellite orbital and thrust parameters simultaneously. The observations from the IGS Multi-Global Navigation Satellite System (GNSS) Experiment (MGEX) network and ultra-rapid products of the German Research Center for Geosciences (GFZ) are used for orbit determination of maneuvered satellites from Sep to Nov 2017. The results show that for the rapidly recovered ephemerides, the average orbit-only SISREs are 1.15 and 1.0 m 1 h after maneuvering for GEO and IGSO respectively, which is comparable to the accuracy of Beidou broadcast ephemerides in normal cases.en_US
dcterms.accessRightsopen accessen_US
dcterms.bibliographicCitationRemote sensing, 2019, v. 11, no. 7, 787en_US
dcterms.isPartOfRemote sensingen_US
dcterms.issued2019-
dc.identifier.scopus2-s2.0-85063988095-
dc.identifier.eissn2072-4292en_US
dc.identifier.artn787en_US
dc.description.validate201906 bcmaen_US
dc.description.oaVersion of Recorden_US
dc.identifier.FolderNumberOA_IR/PIRAen_US
dc.description.pubStatusPublisheden_US
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