Qin Zhiwei, Huang Guanwen, Zhang Qin, Wang Le, Yan Xingyuan, Kang Yanchao, Wang Xiaolei, Xie Shichao
College of Geology Engineering and Geomantic, Chang'an University, 126 Yanta Road, Xi'an 710054, China.
School of Earth Sciences and Engineering, Hohai University, 1 Xikang Road, Nanjing 210098, China.
Sensors (Basel). 2019 Jun 13;19(12):2675. doi: 10.3390/s19122675.
Because there are different types of BeiDou constellations with participating geostationary orbit (GEO) and inclined geosynchronous orbit (IGSO) satellites, the maneuvering frequency of BeiDou satellites is higher than that of other navigation systems. The satellite orbital maneuvers lead to orbital parameter failure for several hours from broadcast ephemeris. Due to the missing initial orbit, the maneuvering thrust, and the period of orbital maneuvering, the orbit products of maneuvering satellites cannot be provided by the International Global Navigation Satellite System (GNSS) Service (IGS) and International GNSS Monitoring and Assessment System (iGMAS). In addition, the period of unhealthy status and the orbital parameters of maneuvering satellites in broadcast ephemeris are unreliable, making the detection of orbital maneuver periods more difficult. Here, we develop a method to detect orbital maneuver periods involving two key steps. The first step is orbit prediction of maneuvering satellites based on precise orbit products. The second step is time period detection of orbit maneuvering. The start time detection factor is calculated by backward prediction orbit and pseudo-range observations, and the end time detection factor is calculated by forward prediction orbit and pseudo-range observations. Data of stations from the Multi-GNSS Experiment (MGEX) and iGMAS were analyzed. The results show that the period of orbit maneuvering could be detected accurately for BeiDou GEO and IGSO satellites. In addition, the orbital maneuver period of other GNSS medium Earth orbit (MEO) satellites could also be determined by this method. The results of period detection for orbit maneuvering provide important reference information for precision orbit and clock offset determination during satellite maneuvers.
由于北斗星座包含不同类型的地球静止轨道（GEO）卫星和倾斜地球同步轨道（IGSO）卫星，北斗卫星的机动频率高于其他导航系统。卫星轨道机动会导致广播星历在数小时内出现轨道参数失效。由于缺少初始轨道、机动推力以及轨道机动周期，国际全球导航卫星系统（GNSS）服务（IGS）和国际GNSS监测与评估系统（iGMAS）无法提供机动卫星的轨道产品。此外，广播星历中机动卫星的不健康状态持续时间和轨道参数不可靠，使得轨道机动周期的检测更加困难。在此，我们开发了一种检测轨道机动周期的方法，该方法涉及两个关键步骤。第一步是基于精确轨道产品对机动卫星进行轨道预测。第二步是检测轨道机动的时间段。通过向后预测轨道和伪距观测计算起始时间检测因子，通过向前预测轨道和伪距观测计算结束时间检测因子。对多GNSS实验（MGEX）和iGMAS的测站数据进行了分析。结果表明，对于北斗GEO和IGSO卫星，可以准确检测到轨道机动周期。此外，该方法还可用于确定其他GNSS中地球轨道（MEO）卫星的轨道机动周期。轨道机动周期检测结果为卫星机动期间的精密轨道和钟差确定提供了重要参考信息。
