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

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Chapter 3 Orbit Tracking System and Their Error Budgets ∆N pc satellite phase center correction ∆N tr tropospheric correction ∆N io ionospheric correction ∆Nex external calibration correction. The full correction ∆N is added to the observed number of cycles N . The delivered measured two-way Doppler cycles are already corrected for the ∆N xx and ∆N sa by the PRARE Master Station. The values of these two corrections are not known from the data files. For orbit determination purposes the only corrections to be considered are ∆Nga , ∆Npc , ∆Nmc , ∆Ntr , ∆Nio and ∆Nex . 3.2.2.2 Error Budget The error budget of PRARE for range measurement is listed in Table 3-4. Actual accuracy of orbit determination of ERS satellite using PRARE is drawn in Figure 3-5 and Figure 3-6. Table 3-4 Error Budget for PRARE (Reigber et al, 1989, 1997; Flechtner, 2000) ERROR SOURCE ERROR (cm) Ionosphere 1.0 Troposphere 2.0-5.0 Calibration 1.5-2.0 Phase and Mass Center 1.0 Total (1σ) 6.5 Figure 3-5 PRARE Measurement residual (From ESOC Homepage: http:\\nng.esoc.esa.de\ers\prare\resip.html) 26
Chapter 3 Orbit Tracking System and Their Error Budgets Figure 3-6 ERS PRARE vs Precise Orbit Comparison (From ESOC Homepage: http:\\nng.esoc.esa.de\ers\prare\ocompo.html) PRARE is an autonomous, space-borne, all-weather, dual frequency, two-way microwave system with ranging and ranging rate measurements for application of high-precision orbit determination. The ground station network is operated continuously and is fully automatic. The time errors are significantly reduced using two way measurements. The most part of the ionospheric error can be eliminated using dual frequency measurements. In addition, PRARE can also determine the position of the ground stations. A disadvantage is, that the use of two-way measurements can also increase the propagation errors. The principle error sources limiting accuracy of PRARE system is the error produced by the atmospheric refraction effects and internal delays. In principle, PRARE can be used for orbit determination of GNSS-2 satellites, but has some problems like DORIS, i.e. low accuracy of Doppler measurements for GEO and IGSO satellites. 3.2.3 Inter-Satellite-Links (ISL) 3.2.3.1 Principle Inter-Satellite-Links require at least two satellites. One satellite is called orbiting platform, for which the orbit should be determined using other tracking systems, usually ground-based tracking systems. Another is user satellite the orbit of which will be determined by orbiting platform satellite. One- and/or two-way observations among satellites have been used so far to measure their relative position and velocity. At present, two models of ISL exist, a low-low model and a high-low model. The low-low model is used for satellites flying at low altitude, i.e. a few hundred of kilometers apart. The main satellite (the orbiting platform) tracks two or more user satellites. The high-low model describes the situation, where a high orbiting satellite carries an intersatellite measurement device that tracks a low orbiting satellite. The coverage for the high-low model is substantially smaller than that for the low-low model, only about 1/5 of the coverage of a low-low configuration (Mueller et al, 1988, Blaha 1991, Feltman 1999). The first application of high-low intersatellite links between two satellites in orbit around the Earth started in April 1975 with a tracking experiment between the geostationary ATS-6 satellite and GEOS-3 at an altitude of 840 kilometer (Schmid et al., 1975). The ISL data has been used for the orbit computation of the low altitude satellites. During this experiment both one-way and two-way range and range-rate data were obtained over the 27
Page 1: PRECISE ORBIT DETERMINATION OF GLOB
Page 4 and 5: Summary GNSS-2 (Global Navigation S
Page 6 and 7: 3.2.2.1 Principle..................
Page 8 and 9: 9.3.3 The Effect of Distribution of
Page 10 and 11: Chapter 1 Introduction 1.2 Developm
Page 12 and 13: Chapter 2 Observations of Orbit Det
Page 26 and 27: Chapter 3 Orbit Tracking System and
Page 40 and 41: Chapter 4 Major Error Sources of Sa
Page 52 and 53: Chapter 5 Perturbation Models of IG
Page 74 and 75: Chapter 6 Algorithms of Orbit Deter
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Chapter 6 Algorithms of Orbit Deter
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Chapter 7 Orbit Determination Using
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Chapter 8 Geostationary Orbit Deter
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Chapter 9 Software and Simulation R
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Conclusion 144
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References Carpino M. (1995): SAEG
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References Klobuchar, J. A.(1996):
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References Traquilla, J. M. and J.
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Acknowledgments 152
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