GNSS-Based Precise Orbit Determination of LEO Satellites Using Double-Differenced Observations

2017 ◽  
Author(s):  
Zhigui Kang ◽  
Byron Tapley ◽  
Sinivas Bettadpur
Keyword(s):  
Orbit Determination ◽  
Precise Orbit Determination ◽  
Precise Orbit ◽  
Leo Satellites

Research on the impact factors of GRACE precise orbit determination by dynamic method

2018 ◽  
Vol 12 (3) ◽  
pp. 249-257 ◽  
Author(s):  
Nan-nan Guo ◽  
Xu-hua Zhou ◽  
Kai Li ◽  
Bin Wu
Keyword(s):  
Orbit Determination ◽  
Precise Orbit Determination ◽  
Sampling Interval ◽  
Satellite Clock ◽  
Position Accuracy ◽  
Precise Orbit ◽  
Clock Error ◽  
Leo Satellites ◽  
Satellite Clock Error

Abstract With the successful use of GPS-only-based POD (precise orbit determination), more and more satellites carry onboard GPS receivers to support their orbit accuracy requirements. It provides continuous GPS observations in high precision, and becomes an indispensable way to obtain the orbit of LEO satellites. Precise orbit determination of LEO satellites plays an important role for the application of LEO satellites. Numerous factors should be considered in the POD processing. In this paper, several factors that impact precise orbit determination are analyzed, namely the satellite altitude, the time-variable earth’s gravity field, the GPS satellite clock error and accelerometer observation. The GRACE satellites provide ideal platform to study the performance of factors for precise orbit determination using zero-difference GPS data. These factors are quantitatively analyzed on affecting the accuracy of dynamic orbit using GRACE observations from 2005 to 2011 by SHORDE software. The study indicates that: (1) with the altitude of the GRACE satellite is lowered from 480 km to 460 km in seven years, the 3D (three-dimension) position accuracy of GRACE satellite orbit is about 3∼4 cm based on long spans data; (2) the accelerometer data improves the 3D position accuracy of GRACE in about 1 cm; (3) the accuracy of zero-difference dynamic orbit is about 6 cm with the GPS satellite clock error products in 5 min sampling interval and can be raised to 4 cm, if the GPS satellite clock error products with 30 s sampling interval can be adopted. (4) the time-variable part of earth gravity field model improves the 3D position accuracy of GRACE in about 0.5∼1.5 cm. Based on this study, we quantitatively analyze the factors that affect precise orbit determination of LEO satellites. This study plays an important role to improve the accuracy of LEO satellites orbit determination.

Efficient precise orbit determination of LEO satellites using GPS

2002 ◽  
Vol 30 (2) ◽  
pp. 295-300 ◽  
Author(s):  
H. Bock ◽  
U. Hugentobler ◽  
T.A. Springer ◽  
G. Beutler
Keyword(s):  
Orbit Determination ◽  
Precise Orbit Determination ◽  
Precise Orbit ◽  
Leo Satellites

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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