Precise Orbit Determination of Global Navigation Satellite System of ...

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Chapter 9 Software and Simulation Results Index of Tracking Stations Index of Tracking Stations Index of Tracking Stations 8 7 6 5 4 3 2 1 8 7 6 5 4 3 2 1 0 0 2 4 6 8 10 12 14 16 18 20 22 24 8 7 6 5 4 3 2 1 Tim e (hour) Figure 9-5 Visibility of an IGSO Satellite at λ=-10° 0 0 2 4 6 8 10 12 14 16 18 20 22 24 Time (hour) Figure 9-6 Visibility of an IGSO Satellite at λ=20° 0 0 2 4 6 8 10 12 14 16 18 20 22 24 Tim e (hour) Figure 9-7 Visibility of an IGSO Satellite at λ=60° 116
Chapter 9 Software and Simulation Results Index of Tracking Stations 8 7 6 5 4 3 2 1 0 0 2 4 6 8 10 12 14 16 18 20 22 24 Time (hour) Figure 9-8 Visibility of a GEO Satellite at λ=20° 9.2 The Simulation Results of Dynamic Orbit Determination using Code Range Observations Figure 9-9 shows the results of dynamic orbit determination using the algorithms, the tracking stations and software GEOKAL as discussed in former chapters and above. Figure 9-9 The accuracy of orbit determination using Kalman filter and 8 tracking stations In Figure 9-9, about 10 days arc length of theoretical orbit has been produced. The satellite positions and velocities of theoretical orbit in the first epoch are chosen as initial orbit parameters for orbit determination. The initial orbit parameters are intentionally added with ±200 meter errors in the position and ±0.1 m/s errors in the velocity. Figure 9-9 shows the accuracy of orbit determination using Kalman filter for about 10 days arc length. The horizontal axis in the figure is time and the vertical axis is the difference between the theoretical orbit and the orbit determined by Kalman filter. From Figure 9-9 it can be seen that using Kalman filter discussed in the chapters 6 and 8, tracking stations presented in §9.1.2, the accuracies of x, y and z coordinates of the satellite orbit determination are about ±0.24, ±0.17, ±0.18 m respectively. In the results above, the satellite visibility is not considered in the orbit determination software GEOKAL. Under this situation it is assumed that the satellites 117
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PRECISE ORBIT DETERMINATION OF GLOB
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Summary GNSS-2 (Global Navigation S
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3.2.2.1 Principle..................
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9.3.3 The Effect of Distribution of
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Chapter 1 Introduction 1.2 Developm
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Chapter 2 Observations of Orbit Det
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Chapter 3 Orbit Tracking System and
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Chapter 4 Major Error Sources of Sa
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Chapter 5 Perturbation Models of IG
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Page 154 and 155: References Carpino M. (1995): SAEG
Page 156 and 157: References Klobuchar, J. A.(1996):
Page 158 and 159: References Traquilla, J. M. and J.
Page 160 and 161: Acknowledgments 152
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