Please use this identifier to cite or link to this item:
http://hdl.handle.net/10397/80857
DC Field | Value | Language |
---|---|---|
dc.contributor | Department of Building and Real Estate | en_US |
dc.creator | Qiao, J | en_US |
dc.creator | Chen, W | en_US |
dc.creator | Ji, S | en_US |
dc.creator | Weng, D | en_US |
dc.date.accessioned | 2019-06-27T06:36:08Z | - |
dc.date.available | 2019-06-27T06:36:08Z | - |
dc.identifier.uri | http://hdl.handle.net/10397/80857 | - |
dc.language.iso | en | en_US |
dc.publisher | Molecular 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.rights | The 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/rs11070787 | en_US |
dc.subject | Beidou | en_US |
dc.subject | Broadcast ephemeris | en_US |
dc.subject | Maneuver detection | en_US |
dc.subject | Thrust force | en_US |
dc.title | Accurate and rapid broadcast ephemerides for Beidou-maneuvered satellites | en_US |
dc.type | Journal/Magazine Article | en_US |
dc.identifier.volume | 11 | en_US |
dc.identifier.issue | 7 | en_US |
dc.identifier.doi | 10.3390/rs11070787 | en_US |
dcterms.abstract | The 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.accessRights | open access | en_US |
dcterms.bibliographicCitation | Remote sensing, 2019, v. 11, no. 7, 787 | en_US |
dcterms.isPartOf | Remote sensing | en_US |
dcterms.issued | 2019 | - |
dc.identifier.scopus | 2-s2.0-85063988095 | - |
dc.identifier.eissn | 2072-4292 | en_US |
dc.identifier.artn | 787 | en_US |
dc.description.validate | 201906 bcma | en_US |
dc.description.oa | Version of Record | en_US |
dc.identifier.FolderNumber | OA_IR/PIRA | en_US |
dc.description.pubStatus | Published | en_US |
Appears in Collections: | Journal/Magazine Article |
Files in This Item:
File | Description | Size | Format | |
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Qiao_Accurate_rapid_broadcast.pdf | 3.51 MB | Adobe PDF | View/Open |
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