Real‐time detection of BDS orbit manoeuvres based on the combination of GPS and BDS observations. Issue 10 (1st October 2020)

• Record Type: Journal Article
• Authors: Tu, Rui; Zhang, Rui; Liu, Zhanke; Fan, Lihong; Han, Junqiang; Zhang, Pengfei; Hong, Ju; Liu, Jinhai; Lu, Xiaochun
• Is Part Of: IET radar, sonar & navigation. Volume 14:Issue 10(2020)
• Page Start: 1603
• Page End: 1609
• Publication Date: 2020-10-01
• Subjects: Global Positioning System -- artificial satellites -- object detection; BDS orbit manoeuvre detection method -- Global Positioning System -- single BDS system -- orbital manoeuvre -- observation time -- real‐time detection -- Chinese BeiDou navigation satellite system -- timing services -- BDS satellites -- continuous PNT services -- reliable PNT services -- geostationary orbit -- global positioning, navigation, and timing services -- inclined geosynchronous -- medium earth orbit -- MEO -- combined GPS‐BDS system -- receiver clock error bias -- time 157.0 min; Signal processing -- Periodicals; Radar -- Periodicals; Sonar -- Periodicals; Electronics in navigation -- Periodicals; Navigation -- Periodicals; 621.3848
• DOI: 10.1049/iet-rsn.2020.0171
• Languages: English
• ISSNs: 1751-8784

Abstract

Abstract : The construction of the third generation of the Chinese BeiDou navigation satellite system (BDS), which provides global positioning, navigation, and timing (PNT) services, will be completed in 2020. As BDS satellites contain the geostationary orbit (GEO), inclined geosynchronous (IGSO), and medium earth orbit (MEO), orbital manoeuvres occur more frequently. Thus, orbit manoeuvre detection is important for continuous and reliable PNT services. A BDS orbit manoeuvre detection method based on the combination of global positioning system (GPS) and BDS observations is proposed in this study. The standard deviations of the observation residuals of the epoch‐differenced velocity estimation of the single BDS system and combined GPS + BDS system were compared to determine the beginning and end of the orbit manoeuvre. The results show that the orbital manoeuvre leads to a position, velocity, and receiver clock error bias of approximately tens to hundreds of metres, several centimetres per second, and tens to hundreds of metres, respectively. Based on the proposed method, the start and end times can be detected in real time and the usable observation time can be extended by >157 min.