Bernese GPS Software Version 5.0 - Bernese GNSS Software

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2. Fundamentals Table 2.9: Perturbing accelerations acting on a GNSS satellite. Perturbation Acceleration Orbit Error m/s 2 after one Day (m) Two-Body Term of Earth’s Gravity Field 0.59 ∞ Oblateness of the Earth 5 · 10 −5 10 ′ 000 Lunar Gravitational Attraction 5 · 10 −6 3000 Solar Gravitational Attraction 2 · 10 −6 800 Other Terms of Earth’s Gravity Field 3 · 10 −7 200 Radiation Pressure (direct) 9 · 10 −8 200 Y-Bias 5 · 10 −10 2 Solid Earth Tides 1 · 10 −9 0.3 velocity vectors, ${LG}/EPHEM.f is used for computing these vectors from the elements. The osculating orbit (defined by the osculating elements) at time t is tangential to the actual orbit at time t. The actual orbit in a time interval [t1,t2] is the envelope of all the osculating orbits in this interval. The following Figures 2.9 to 2.13 show the osculating elements (except u0) for GPS satellite PRN 25 over a time interval of three days in the year 2003. We see very pronounced short-period perturbations (with periods of one satellite revolution or half a revolution), most of them caused by the Earth’s oblateness. Moreover we see secular perturbations in the right ascension of the ascending node Ω of about −15 o per year and long-period perturbations with periods of half a month for the inclination i (in addition to the short-period perturbations). From these perturbations in the elements we conclude that it is very convenient to think of the actual orbit as a time-series of osculating elements. We may, e.g., follow very nicely the precession of the orbital plane and we have the impression that there are only short-period perturbations in the semimajor axis a. That there are more complex perturbations involved becomes obvious if we study the mean elements (mean values of the elements over one nodal revolution of the satellite) over longer time intervals. Figure 2.14 shows the development of the mean semimajor axis for PRN 25 over nine years (1995 to 2003). Figure 2.14 illustrates an essential characteristic of the GPS: there are very pronounced very long-periodic perturbations of the semimajor axes a of the satellites which are actually due to the resonance terms of the Earth’s gravity field [Ineichen et al., 2003b]. These resonance perturbations require relatively frequent station keeping maneuvers for the GPS satellites (about once per year). We see nine such events in Figure 2.14. Without maneuvers (along-track pulses) the distribution of the satellites within the orbital plane could not be maintained uniform for a long period of time. It is worth mentioning that GLONASS satellites do not show a similar resonance behavior due to their different orbital period. Station keeping maneuvers of GLONASS satellites are, therefore, not necessary. At the CODE Analysis Center maneuvers of GPS satellites are detected automatically and epoch and velocity change of the events is estimated since November 2003. Until end of July 2006 a total of 65 repositioning events were identified with velocity changes between 50 and 3000 mm/s. Page 28 AIUB
Semimajor axis [km] - 26560 km 1.5 1.0 0.5 0.0 -0.5 -1.0 -1.5 -2.0 -2.5 338 338.5 339 339.5 340 340.5 341 Doy in 2003 2.2 GNSS Satellite Orbits Figure 2.9: Osculating semimajor axis of PRN 25 during three days of year 2003. Eccentricity 0.01086 0.01085 0.01084 0.01083 0.01082 0.01081 0.01080 0.01079 0.01078 0.01077 0.01076 0.01075 338 338.5 339 339.5 340 340.5 341 Doy in 2003 Figure 2.10: Osculating eccentricity of PRN 25 during three days of year 2003. Inclination [deg] 54.060 54.059 54.058 54.057 54.056 54.055 54.054 54.053 54.052 338 338.5 339 339.5 340 340.5 341 Doy in 2003 Figure 2.11: Osculating inclination of PRN 25 during three days of year 2003. Bernese GPS Software Version 5.0 Page 29
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Bernese GPS Software Version 5.0 Ed
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Bernese GPS Software Version 5.0 As
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Page 22 and 23: List of Figures 5.1 Flow diagram of
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4. Import and Export of External Fi
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5. Preparation of Earth Orientation
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6. Data Preprocessing Preprocessing
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6. Data Preprocessing (a) AS turned
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6. Data Preprocessing 6.2.4 Code Sm
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6. Data Preprocessing is set to 2.
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6. Data Preprocessing 6.3.2 Preproc
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6. Data Preprocessing RMS of kin. s
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6. Data Preprocessing The ambiguiti
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6. Data Preprocessing no loss of si
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6. Data Preprocessing This epoch-di
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6. Data Preprocessing (e.g., from C
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6. Data Preprocessing The second pa
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6. Data Preprocessing GAR small pie
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6. Data Preprocessing -------------
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6. Data Preprocessing automated pro
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6. Data Preprocessing 6.6.2 Generat
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6. Data Preprocessing 6.6.3 Detect
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6. Data Preprocessing (6) If the to
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7. Parameter Estimation p u × 1 ve
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7. Parameter Estimation The two bas
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7. Parameter Estimation contains a
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7. Parameter Estimation The binary
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7. Parameter Estimation 7.5.2 Piece
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7. Parameter Estimation The equatio
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7. Parameter Estimation 7.5.4.4 Fix
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7. Parameter Estimation where Q 11
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7. Parameter Estimation consequence
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7. Parameter Estimation are address
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7. Parameter Estimation ... ! Pre-p
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7. Parameter Estimation The RINEX m
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7. Parameter Estimation In a succes
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7. Parameter Estimation Page 166 AI
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8. Initial Phase Ambiguities and Am
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9. Combination of Solutions 9.2 Seq
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9. Combination of Solutions Substit
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9. Combination of Solutions We may
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9. Combination of Solutions files a
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9. Combination of Solutions x x 1 t
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9. Combination of Solutions Both re
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9. Combination of Solutions 9.4 The
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9. Combination of Solutions 9.4.2 G
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9. Combination of Solutions Excepti
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9. Combination of Solutions As alre
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9. Combination of Solutions Table 9
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9. Combination of Solutions The poi
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9. Combination of Solutions (2) Tra
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9. Combination of Solutions Step 1:
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10. Station Coordinates and Velocit
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11. Troposphere Modeling and Estima
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12. Ionosphere Modeling and Estimat
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13. Differential Code Biases Promin
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13. Differential Code Biases Figure
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13. Differential Code Biases ======
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13. Differential Code Biases Page 2
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14. Clock Estimation τ (BRUS-PTBB)
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14. Clock Estimation Here the limit
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14. Clock Estimation to zero. All c
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14. Clock Estimation #OBS : Number
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14. Clock Estimation 14.3 Clock RIN
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14. Clock Estimation cessed if CCRN
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14. Clock Estimation RINEX files th
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14. Clock Estimation the clock valu
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14. Clock Estimation SINGLE POINT P
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14. Clock Estimation Page 308 AIUB
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15. Estimation of Satellite Orbits
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16. Antenna Phase Center Offsets an
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17. Data Simulation Tool GPSSIM 17.
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17. Data Simulation Tool GPSSIM The
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17. Data Simulation Tool GPSSIM The
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17. Data Simulation Tool GPSSIM Res
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18. The Menu System 18.2 Starting t
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18. The Menu System 18.3.1 Menu Bar
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18. The Menu System 18.3.5 Panel Co
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18. The Menu System the menu the ne
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18. The Menu System Table 18.1: Pre
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18. The Menu System 18.5.3 System E
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18. The Menu System 18.7 Change Opt
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18. The Menu System 18.9 Technical
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18. The Menu System ... ! Environme
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18. The Menu System The keyword ENV
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18. The Menu System ! List of Remai
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18. The Menu System The MENUAUX-mec
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18. The Menu System Keyword values
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19. Bernese Processing Engine (BPE)
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20. Processing Examples inspect the
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20. Processing Examples 20.3.1 How
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20. Processing Examples • (option
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20. Processing Examples PID 111 PRE
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20. Processing Examples 20.4.1.7 Cr
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20. Processing Examples 20.4.2.1 Co
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20. Processing Examples PID 313 MPR
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20. Processing Examples Further rea
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20. Processing Examples # # Create
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20. Processing Examples PID 101 GPS
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20. Processing Examples The RINEX n
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20. Processing Examples # # Preproc
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20. Processing Examples the loop, d
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20. Processing Examples PID 903 CLK
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20. Processing Examples and IGS 00B
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20. Processing Examples • Save th
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20. Processing Examples PID 321 GPS
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20. Processing Examples PID 301 CLK
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21. Program Structure $C / %C% PGM
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21. Program Structure (program GPSE
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21. Program Structure continued fro
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21. Program Structure ! -----------
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22. Data Structure "Program" Area $
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22. Data Structure Table 22.1: List
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22. Data Structure 22.4.2 Geodetic
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22. Data Structure 22.4.4 Antenna P
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22. Data Structure 22.4.5 Satellite
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22. Data Structure 22.4.6 Satellite
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22. Data Structure DIFFERENCE OF GP
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22. Data Structure 22.4.9 Subdaily
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22. Data Structure EGM96 EGM96, VER
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22. Data Structure SINEX : OPTION I
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22. Data Structure 22.4.16 Panel Up
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22. Data Structure 22.6.2 Header an
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22. Data Structure 15 Antenna type(
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22. Data Structure SVN-NUMBER= 2 ME
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22. Data Structure -1 2 1 5 TITLE :
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22. Data Structure Used by: ORBGEN
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22. Data Structure 53064.00 53065.0
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22. Data Structure CODE’S MONTHLY
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22. Data Structure Table 22.4: Stat
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22. Data Structure (3) TYPE 003: HA
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22. Data Structure 22.8.4 Station P
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22. Data Structure Remarks: • Eac
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22. Data Structure The following st
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22. Data Structure Table 22.7: List
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22. Data Structure AJAC $$ FES2004
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22. Data Structure Station sigma fi
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22. Data Structure GOPE 11502M002 Z
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22. Data Structure 22.8.18 Receiver
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22. Data Structure CODE RAPID 3-DAY
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22. Data Structure 22.9.3 Meteo and
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22. Data Structure IONOSPHERE MODEL
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22. Data Structure 22.10 Miscellane
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22. Data Structure 22.10.4 Variance
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22. Data Structure 22.10.5 Normal E
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22. Data Structure 22.10.7 Observat
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22. Data Structure Created by: Each
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22. Data Structure ----------------
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22. Data Structure 22.10.17 BPE log
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23. Installation Guide 23.1.2 Conte
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23. Installation Guide 23.1.3.2 Ins
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23. Installation Guide BERN50 : $C
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23. Installation Guide If you have
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23. Installation Guide To make the
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23. Installation Guide List of Inst
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23. Installation Guide 23.2.4 Confi
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23. Installation Guide Configure me
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23. Installation Guide ${P}/EXAMPLE
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23. Installation Guide To recompile
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23. Installation Guide Page 574 AIU
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24. The Step from Version 4.2 to Ve
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BIBLIOGRAPHY Bock, H. (2004), Effic
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BIBLIOGRAPHY Janes, H. W., R. B. La
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BIBLIOGRAPHY Schaer, S. (1998), COD
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BIBLIOGRAPHY Page 588 AIUB
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INDEX OF PROGRAMS NEQ2ASC, 207, 541
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Index of Program Panels CODSPP 2: I
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Index of Program Panels MKCLUS 3: R
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INDEX OF KEYWORDS Antenna verificat
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INDEX OF KEYWORDS Cluster definitio
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INDEX OF KEYWORDS variance-covarian
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INDEX OF KEYWORDS orbit products, 1
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INDEX OF KEYWORDS Multi-session sol
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INDEX OF KEYWORDS Orbital elements
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INDEX OF KEYWORDS Receiver antenna
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INDEX OF KEYWORDS orbit modeling, 9
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INDEX OF KEYWORDS WGS-84, 19, 88, 2
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