Ground track maintenance for BeiDou IGSO satellites subject to tesseral resonances and the luni-solar perturbations

Fan, Li‐Zhen; Jiang, Chao; Hu, Min

doi:10.1016/j.asr.2016.09.014

Cited by 14 publications

(2 citation statements)

References 7 publications

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“…As an important Chinese navigation satellite constellation, BDS has attracted extensive attention from researchers around the world (Montenbruck et al, 2013;Zhao et al, 2015;Fan et al, 2017;Tang et al, 2017;Xie et al, 2017;Li et al, 2018;Kuznetsov and Avvakumova, 2019;Lin et al, 2020;Tan et al, 2022;Huang et al, 2022). In this paper, the effect of the initial orbital elements on the long-term evolution of the MEO BDS-3 satellite, considering the lunisolar secular resonance, is systematically studied.…”

Section: Introductionmentioning

confidence: 99%

Effect of initial orbital elements on orbital evolution of MEO BDS-3 satellite with considering the lunisolar secular resonance

Wang,

Meng,

Feng

et al. 2024

Preprint

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This paper investigates the effect of initial orbital elements on the orbital evolution of the Medium Earth Orbit (MEO) satellites of the third generation of the BEIDOU Navigation Satellite System (BDS-3), considering the lunisolar secular resonance. The long-term evolution of 24 BDS-3 MEO satellites without active control is simulated by the double-averaged Hamiltonian dynamical model. The simulation results show that some of the satellites could enter the Earth's atmosphere as their eccentricities increase. On the contrary, some other satellites have stable orbits during the long-term evolution. The effects of different e0, i0, ω0, and Ω0 on the long-term evolution are investigated, respectively. The results show that when e0 is larger, the eccentricity reaches emax faster; and the variations in e0 or ω0 don't change the values of the resonance angle in resonance. However, the change of i0 and Ω0 will change the values of the resonance angle in resonance. The maximum eccentricity method is used to study the influences of different initial conditions (including initial orbital elements and initial epoch) on the long-term evolution of MEO satellites. The results show that the changes of i0, omega0, and Omega0 affect the distribution of emax in the (Ω0, ω0) space. In the (Ω0, ω0) space, if the initial ΩM changes, the shape of the emax map changes, but the maximum value of emax barely changes. Apart from the region with large values of emax in the (Ω0, ω0) space, there also exist regions with small values of emax, where the differences between emax and e0 are very small.

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Section: Introductionmentioning

confidence: 99%

Effect of initial orbital elements on orbital evolution of MEO BDS-3 satellite with considering the lunisolar secular resonance

Wang,

Meng,

Feng

et al. 2024

Preprint

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“…Beidou GEO and IGSO satellites are more prone to drift away from their assigned orbit slots [2][3][4]. Moreover, the lunisolar resonance and solar radiation pressure (SRP) also have a perturbation effect for orbits at the geosynchronous distance [5][6][7]. Frequent maneuvers are executed for Beidou GEO and IGSO satellites, generally, about 9 to 15 times per year for each GEO and twice per year for each IGSO, whereas no maneuver was found for Beidou medium earth orbit (MEO) satellites in a one-year period studied [8].…”

Section: Introductionmentioning

confidence: 99%

Accurate and Rapid Broadcast Ephemerides for Beidou-Maneuvered Satellites

Qiao

Chen

et al. 2019

Remote Sensing

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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.

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