Orbital Artifacts in Multi‐GNSS Precise Point Positioning Time Series

Zajdel, Radosław; Kaźmierski, Kamil; Sośnica, Krzysztof

doi:10.1029/2021jb022994

Cited by 6 publications

(2 citation statements)

References 59 publications

(101 reference statements)

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“…All selected stations belong to the Multi-GNSS Experiment (MGEX) pilot project (Kouba 2009;Montenbruck et al 2017) and ensure tracking of three GNSS systems to analyze system-specific clock errors. Zajdel et al (2020Zajdel et al ( , 2022 identified system-specific errors emerging from different aliasing, revolution periods of satellites, and multipath effects in multi-GNSS (GPS, GLONASS, Galileo) solutions. This raises the question of whether similar systematic errors can be identified in the multi-GNSS clock parameters.…”

Section: Introductionmentioning

confidence: 99%

Characteristics of the IGS receiver clock performance from multi-GNSS PPP solutions

2023

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Global navigation satellite system (GNSS) receivers belonging to the International GNSS Service (IGS) are equipped with different types of clocks, such as internal crystal quartz clocks, rubidium and cesium atomic clocks, as well as hydrogen masers. These clocks are characterized by different phase and frequency accuracies and stabilities, resulting in different systematic clock time series patterns. We analyze the clock offsets between different GNSS systems, provide noise characteristics of the undifferenced and differenced clock parameters, and detect systematic patterns of the clocks. The time series of the receiver clocks are dominated by the diurnal, semidiurnal, and sometimes terdiurnal signals with amplitudes up to several meters. Hydrogen masers provide the highest clock stability, and the lowest is by internal clocks. However, there are also groups of very stable internal clocks that perform similarly to low-performing hydrogen masers and rubidium clocks. The interquartile ranges for epoch-differenced clock parameters fall between 3 and 250 mm for the best hydrogen masers and the worst internal clocks, respectively.

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Section: Introductionmentioning

confidence: 99%

Characteristics of the IGS receiver clock performance from multi-GNSS PPP solutions

2023

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“…Accurate modeling of non‐gravitational force is required for the precise orbit determination of LEO satellites (Hackel et al., 2016; Kang et al., 2006; Montenbruck, Hackel, & Jäggi, 2018; Wu et al., 1991), SLR satellites (Appleby et al., 2016; M Pearlman, Arnold, et al., 2019; Zajdel et al., 2022), and GNSS satellites (D. Arnold et al., 2015; Bury et al., 2020; Duan et al., 2020; Montenbruck et al., 2014; Zhao et al., 2022). Solar radiation pressure and atmospheric drag are the two most important non‐gravitational forces acting on LEO satellites.…”

Section: Introductionmentioning

confidence: 99%

Improving Precise Orbit Determination of LEO Satellites Using Enhanced Solar Radiation Pressure Modeling

Wang

Jiang

et al. 2023

Space Weather

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Precise orbit knowledge is a fundamental requirement for low Earth orbit (LEO) satellites. High‐precision non‐gravitational force modeling directly improves the overall quality of LEO precise orbit determination (POD). To address the potential systematic errors in solar radiation pressure (SRP), we introduce observed radiation data and modeled physical effects to describe the real in‐flight environment of satellites. Time‐dependent solar irradiance data and a highly physical shadow model are considered for SRP modeling. We develop an advanced thermal reradiation model for satellite solar panels. A set of improved non‐gravitational force models is performed for LEO POD, and we discuss the benefits of the enhanced dynamic models on orbit quality and dependence on empirical parameters. The Gravity Recovery and Climate Experiment Follow‐On (GRACE‐FO), Jason‐3, and Haiyang‐2B missions are selected for the POD process. Estimated empirical acceleration and scale parameters and independent satellite laser ranging (SLR) are used to validate the final orbit solutions. The magnitude of empirical acceleration estimated in POD is reduced by 19% with the enhanced dynamic modeling, and the estimated scale factor for the SRP converges to stable and reasonable level. Furthermore, the steady‐state temperature model used in thermal reradiation can effectively reduce mismodeled effects in the SRP, and the systematic linear dependency revealed by the SLR residuals is significantly reduced for the GRACE‐C and Jason‐3 satellites, with improvements of approximately 61% and 49%, respectively. Overall, advances are made in the explicit modeling of non‐gravitational forces to pursue superior satellite orbits, suggesting a more dynamic orbit solution.

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