scholarly journals Precise orbit determination of Haiyang-2 using satellite laser ranging

2012 ◽  
Vol 58 (6) ◽  
pp. 589-597 ◽  
Author(s):  
Gang Zhao ◽  
XuHua Zhou ◽  
Bin Wu
Keyword(s):  
Orbit Determination ◽  
Precise Orbit Determination ◽  
Satellite Laser Ranging ◽  
Laser Ranging ◽  
Precise Orbit

scholarly journals GLONASS precise orbit determination with identification of malfunctioning spacecraft

GPS Solutions ◽  
2022 ◽  
Vol 26 (2) ◽  
Author(s):  
Grzegorz Bury ◽  
Krzysztof Sośnica ◽  
Radosław Zajdel ◽  
Dariusz Strugarek
Keyword(s):  
Analytical Model ◽  
Orbit Determination ◽  
Precise Orbit Determination ◽  
Systematic Errors ◽  
Satellite Laser Ranging ◽  
Laser Ranging ◽  
Precise Orbit ◽  
Similar Construction ◽  
Wing Model ◽  
The Impact

AbstractDue to the continued development of the GLONASS satellites, precise orbit determination (POD) still poses a series of challenges. This study examines the impact of introducing the analytical tube-wing model for GLONASS-M and the box-wing model for GLONASS-K in a series of hybrid POD strategies that consider both the analytical model and a series of empirical parameters. We assess the perturbing accelerations acting on GLONASS spacecraft based on the analytical model. All GLONASS satellites are equipped with laser retroreflectors for satellite laser ranging (SLR). We apply the SLR observations for the GLONASS POD in a series of GNSS + SLR combined solutions. The application of the box-wing model significantly improves GLONASS orbits, especially for GLONASS-K, reducing the STD of SLR residuals from 92.6 to 27.6 mm. Although the metadata for all GLONASS-M satellites reveal similar construction characteristics, we found differences in empirical accelerations and SLR offsets not only between GLONASS-M and GLONASS-M+ but also within the GLONASS-M+ series. Moreover, we identify satellites with inferior orbit solutions and check if we can improve them using the analytical model and SLR observations. For GLONASS-M SVN730, the STD of the SLR residuals for orbits determined using the empirical solution is 48.7 mm. The STD diminishes to 41.2 and 37.8 mm when introducing the tube-wing model and SLR observations, respectively. As a result, both the application of the SLR observations and the analytical model significantly improve the orbit solution as well as reduce systematic errors affecting orbits of GLONASS satellites.

Mass density of the upper atmosphere derived from Starlette’s Precise Orbit Determination with Satellite Laser Ranging

2010 ◽  
Vol 332 (2) ◽  
pp. 341-351 ◽  
Author(s):  
H. S. Jeon ◽  
S. Cho ◽  
Y. S. Kwak ◽  
J. K. Chung ◽  
J. U. Park ◽  
...  
Keyword(s):  
Orbit Determination ◽  
Mass Density ◽  
Precise Orbit Determination ◽  
Upper Atmosphere ◽  
Satellite Laser Ranging ◽  
Laser Ranging ◽  
Precise Orbit

scholarly journals A Second-Order Time-Difference Position Constrained Reduced-Dynamic Technique for the Precise Orbit Determination of LEOs Using GPS

2021 ◽  
Vol 13 (15) ◽  
pp. 3033
Author(s):  
Hui Wei ◽  
Jiancheng Li ◽  
Xinyu Xu ◽  
Shoujian Zhang ◽  
Kaifa Kuang
Keyword(s):  
Orbit Determination ◽  
Dynamic Models ◽  
Precise Orbit Determination ◽  
Second Order ◽  
Time Difference ◽  
Error Sources ◽  
Precise Orbit ◽  
Unmodeled Dynamic ◽  
Reduced Dynamic

In this paper, we propose a new reduced-dynamic (RD) method by introducing the second-order time-difference position (STP) as additional pseudo-observations (named the RD_STP method) for the precise orbit determination (POD) of low Earth orbiters (LEOs) from GPS observations. Theoretical and numerical analyses show that the accuracies of integrating the STPs of LEOs at 30 s intervals are better than 0.01 m when the forces (<10−5 ms−2) acting on the LEOs are ignored. Therefore, only using the Earth’s gravity model is good enough for the proposed RD_STP method. All unmodeled dynamic models (e.g., luni-solar gravitation, tide forces) are treated as the error sources of the STP pseudo-observation. In addition, there are no pseudo-stochastic orbit parameters to be estimated in the RD_STP method. Finally, we use the RD_STP method to process 15 days of GPS data from the GOCE mission. The results show that the accuracy of the RD_STP solution is more accurate and smoother than the kinematic solution in nearly polar and equatorial regions, and consistent with the RD solution. The 3D RMS of the differences between the RD_STP and RD solutions is 1.93 cm for 1 s sampling. This indicates that the proposed method has a performance comparable to the RD method, and could be an alternative for the POD of LEOs.

scholarly journals Evaluation of DTRF2014, ITRF2014, and JTRF2014 by Precise Orbit Determination of SLR Satellites

2018 ◽  
Vol 56 (6) ◽  
pp. 3148-3158 ◽  
Author(s):  
Sergei Rudenko ◽  
Mathis BloBfeld ◽  
Horst Muller ◽  
Denise Dettmering ◽  
Detlef Angermann ◽  
...  
Keyword(s):  
Orbit Determination ◽  
Precise Orbit Determination ◽  
Precise Orbit
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