A Method to Determine BeiDou GEO/IGSO Orbital Maneuver Time Periods.

Zhiwei Qin,Xiaolei Wang,Shichao Xie,Qin Zhang,Le Wang,Yanchao Kang,Xingyuan Yan,Guanwen Huang

doi:10.3390/s19122675

Zhiwei Qin, Xiaolei Wang + Show 6 more

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https://doi.org/10.3390/s19122675

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Abstract

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.

Highlights

The development of the BeiDou Navigation Satellite System (BDS) of China was planned in three steps: an experimental system, a regional system, and a global system [1]
In order order to to limit limit the length of the paper and reduce duplication of text, the results of the satellite orbit the length of the paper and reduce duplication of text, the results of the inclined geosynchronous orbit (IGSO) and medium Earth orbit (MEO) satellite orbit maneuver given
059–061) inthe (a).orbit maneuvering periods of IGSO and MEO satellites can be detected by the proposed method in this study

Summary

Introduction

The development of the BeiDou Navigation Satellite System (BDS) of China was planned in three steps: an experimental system, a regional system, and a global system [1]. The satellites constellation of BDS consists of a geostationary orbits (GEO: C01, C02, C03, C04, C05), inclined geosynchronous orbits (IGSO: C06, C07, C08, C09, C10, C13), and medium Earth orbits (MEO: C11, C12, C14). BDS applications across the Asia-Pacific region [2,3,4,5,6] They bring great challenges to orbit determination, especially for GEO satellites with the demand of geostationary orbit. In order to maintain the geosynchronous characteristics of the GEO and IGSO satellites, their frequency of orbit. The dynamic models for determining the orbit are different during maneuvering and non-maneuvering periods. Because the period of orbit maneuvering is unknown, the precise orbits of satellites cannot be determined during the non-maneuvering period. It is necessary to develop an approach for detecting satellite orbit maneuvering periods with good time resolution

Methods

Results

Conclusion