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

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Chapter 9 Software and Simulation Results 9.3.4 Orbit Determination With Integer Ambiguity Solution Due to propagation errors, satellite clock drift and receiver noises, it is difficult to fix the initial ambiguities of carrier phase observations into integers during data processing for orbit determination. What accuracy of dynamic orbit determination can be achieved if the initial integer ambiguities of carrier phase observable are resolved? Figure 9-66 to Figure 9-69 show the results (sample rate =10min). Ambiguities Difference (meter) 200 180 160 140 120 100 80 60 40 20 0 -20 -40 -60 2 1,5 1 0,5 0 -0,5 -1 -1,5 -2 0 24 48 72 96 120 144 168 192 216 240 Tim e (hour) Figure 9-61 Integer Ambiguity Solutions 0 24 48 72 96 120 Time (hour) 144 168 192 216 240 Figure 9-62 Accuracy of Orbit Determination of an IGSO Satellite at λ=-10° with Integer Ambiguity Solution 140 dx dy dz
Chapter 9 Software and Simulation Results Difference (meter) Difference (meter) 2 1,5 1 0,5 0 -0,5 -1 -1,5 -2 0 24 48 72 96 120 Time (hour) 144 168 192 216 240 Figure 9-63 Accuracy of Orbit Determination of an IGSO Satellite at λ=20° with Integer Ambiguity Solution 2 1,5 1 0,5 0 -0,5 -1 -1,5 -2 0 24 48 72 96 120 Time (hour) 144 168 192 216 240 Figure 9-64 Accuracy of Orbit Determination of an IGSO Satellite at λ=60° with Integer Ambiguity Solution Figure 9-61 shows that data processing for 45 h 20 m , all initial ambiguities of observations are fixed into integers. Figure 9-62, Figure 9-63 and Figure 9-64 show the promising accuracy of dynamic orbit determination of IGSO and GEO satellites. According to statistics from the differences between Kalman filter and theoretical error-free orbits, the accuracy of coordinate components of dynamic orbit determination of an IGSO satellite located at λ=- 10° are ±0.01 m, ±0.01 m and ±0.01 m respectively; the accuracy of an IGSO satellite located at λ=20° are ±0.02 m, ±0.01 m and ±0.01 m respectively and the accuracy of an IGSO satellite located at λ=60° are ±0.07 m, ±0.05 m and ±0.08 m respectively. From these figures it can also be found that the wave-like variations in the accuracy of orbit determination have been significantly reduced. This means, that with the same error budget the effects of geometrical distribution of tracking station network and observation gaps due to the satellite visibility are largely eliminated. If the signal is lost after centimeter-accuracy of orbit determination has been reached, the initial integer ambiguities of recovered signals will be quickly resolved using high-precise orbit and coordinate of tracking stations, but this method is not suitable for orbit maneuvers. It is difficult to resolve the initial ambiguity of carrier phase observation for GEO satellite, but if the initial ambiguity could be solved using other approaches, the accuracy of orbit determination of a GEO satellite would be significantly increased, see Figure 9-65. 141 dx dy dz dx dy dz
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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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Chapter 6 Algorithms of Orbit Deter
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Chapter 7 Orbit Determination Using
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Chapter 7 Orbit Determination Using
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Page 158 and 159: References Traquilla, J. M. and J.
Page 160 and 161: Acknowledgments 152
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