precise orbit determination for gnss...
TRANSCRIPT
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Issue/Revision: 1.0
Reference:
Status: Approved
ESA UNCLASSIFIED - For Official Use
Precise Orbit Determination for GNSS satellites
E. Schoenemann1, T. Springer2, F. Dilssner3, C. Garcia Serrano4, C. Flohrer2, F. Reichel5, W. Enderle1, R. Zandbergen1 (1) ESA/ESOC, (2) PosiTim@ESOC, (3) CGI@ESOC, (4) GMV@ESOC, (5) TU Darmstadt@ESOC 28/10/2015
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 2
ESA UNCLASSIFIED - For Official Use
Outline
• Introduction • Experimental setup • Exemplary discussion of results • Conclusions
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 3
ESA UNCLASSIFIED - For Official Use
General introduction Motivation
Motivation: Generation of best GNSS Precise Orbit Determination solution for all GNSS satellites Difficulties:
• Reference frames (aligned to ITRF with limited accuracy) • Time scales (aligned to UTC with limited accuracy) • Different signals/frequencies and combinations (different
characteristics, biases) • Satellite properties and characteristics • Different orbit characteristics (altitude, inclination, revolution,
eccentricities)
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 4
ESA UNCLASSIFIED - For Official Use
General introduction Trend in satellite area to mass ratio
Trend in satellite area to mass ratio: • More signals (requiring and emitting more power) • Larger solar panels • Increase of area to mass ratio
More difficult to model: • Antenna thrust • Albedo • Solar radiation pressure
(orbit normal mode needs to be handled properly)
Approx. Area/ mass1)
Est. -D0 (Beta 0)
GPS IIA 0.011 ~93nm/s2
GPS IIRM 0.012 ~99nm/s2 GPS IIR 0.012 ~102nm/s2 GPS IIF 0.018 ~108nm/s2 Galileo 0.019 ~113nm/s2 QZSS 0.020 ~155nm/s2
1) Properties from public available data
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 5
ESA UNCLASSIFIED - For Official Use
General introduction Simplified satellite shape
-Z
+X -Y +Y
+Z
-X
A A
+SA
-SA
+SA
-SA
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 6
ESA UNCLASSIFIED - For Official Use
General introduction Satellite shapes (relationship between box and wing)
1) Properties from public data
max-min [m2] Rank Mass [kg] Impact factor Rank
GPS-IIA 1.3 7 975 0.21 7
GPS-IIR/RM 1.8 6 1100 0.27 4
GPS-IIF 2.3 4 1450 0.26 5
GLONASS-M 2.8 3 1400 0.33 3
Galileo 2.0 5 695 0.46 2
BeiDou 3.2 2 2000 0.26 5
QZSS 12.2 1 2000 1.00 1
10 20 30 40 [m2]
min box max box wings
Difficult to model SRP, if attitude is not accurately known.
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 7
ESA UNCLASSIFIED - For Official Use
GNSS attitude modes
GNSS GPS Yaw steering GLONASS Yaw steering Galileo Yaw steering BeiDou (MEO) Yaw steering / orbit normal BeiDou (IGSO) Yaw steering / orbit normal BeiDou (GEO) Orbit normal QZSS Yaw steering / orbit normal
Difficulty to use estimated solar radiation pressure parameters (empirical models such as CODE, ECOM2) in orbit normal mode.
ESOC decided to use analytical a-priori models (in this case box-wing).
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 8
ESA UNCLASSIFIED - For Official Use
Reprocessing
Approach: Reprocessing of multi-GNSS observation data to analyse data and resulting products and to develop, optimise and test different satellite models. Time period:
• 01. January 2014 – 29 June 2015 Observation data:
• ESOC + JAXA + MGEX tracking network GNSS:
• All available GNSS (GPS, Glonass, Galileo, BeiDou, QZSS) Processing setup:
• Aligned to ESOC IGS processing, but adjusted for multi-GNSS Approach:
• Iterative process, introducing/improving the models step by step
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 9
ESA UNCLASSIFIED - For Official Use
Reprocessing Extract of list of runs performed
First run (as ESOC IGS run (box-wing for GPS+GLONASS)): + All GNSS (Galileo, BeiDou, QZSS)
Second run (as previous run): + Attitude modelling for BeiDou and QZSS
Third run (as previous run): + Box-wing model for all constellations (+CODE parameter)
Forth run (as previous run): + Tuned Box-wing models QZSS and BeiDou (+CODE parameter) + ESOC ANTEX (IGS GPS only + ESOC corrections Galileo, BeiDou,
QZSS)
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 10
ESA UNCLASSIFIED - For Official Use
Phase centre offsets/variations Impact of incorrect PCO offset on POD (BeiDou)
• PCO correction as recommended by MGEX in 2014 (in red) • ESOC estimated PCO/PCV-based solution (in blue)
RMS of orbit overlap differences (3D) Ionosphere free linear combination (B1-B2 & B1-B3)
Dilßner, F. et al.: Estimation of Satellite Antenna Phase Center Corrections for BeiDou. IGS workshop 2014, June 23-27, Pasadena, USA
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 11
ESA UNCLASSIFIED - For Official Use
Impact of analytical SRP models (box-wing) QZSS-01 radial orbit difference (box-wing + CODE vs. CODE)
Argument of Latitude
QZSS-01 (J01) radial orbit difference (box-wing vs. CODE)
Rad
ial o
rbit
differ
ence
(m
m)
Box-wing model generated empirically.
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 12
ESA UNCLASSIFIED - For Official Use
Impact of analytical SRP models (box-wing) QZSS-01 SLR 2-way range residuals (Empirical SRP mod.)
Argument of Latitude
QZSS-01 (J01) SLR 2-way range residuals
SLR
2-w
ay r
ange
res
idua
ls (
m)
Note: Figure shows 2-way SLR residuals!
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 13
ESA UNCLASSIFIED - For Official Use
Impact of analytical SRP models (box-wing) QZSS-01 SLR 2-way range residuals (Box-wing mod.)
Argument of Latitude
QZSS-01 (J01) SLR 2-way range residuals
SLR
2-w
ay r
ange
res
idua
ls (
m)
Note: Figure shows 2-way SLR residuals!
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 14
ESA UNCLASSIFIED - For Official Use
Impact of analytical SRP models (box-wing) QZSS-01 est. CODE D0 parameter (without box-wing mod.)
Beta
QZSS-01 estimated D0 parameter (without box-wing mod.)
Estim
ated
CO
DE
D0
(nm
/s)
Estim
ated
CO
DE
D0
(nm
/s2 )
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 15
ESA UNCLASSIFIED - For Official Use
Impact of analytical SRP models (box-wing) QZSS-01 est. CODE D0 parameter (box-wing mod.)
Beta
QZSS-01 estimated D0 parameter (box-wing mod.)
Estim
ated
CO
DE
D0
(nm
/s)
• D0 reduced by 97%
• Still not zero, but pattern reduced significantly
• Still problems in transition phase and in orbit normal mode
Estim
ated
CO
DE
D0
(nm
/s2 )
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 16
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Impact of analytical SRP models (box-wing) QZSS-01 difference of est. clock to linear fit (daily)
• Orbit error mapped to clock
• Still problems in transition phase and in orbit normal mode
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 17
ESA UNCLASSIFIED - For Official Use
Impact of analytical SRP models (box-wing) QZSS-01 epoch wise clock estimates (CODE vs. box-wing)
Difference to linear fit:
CODE 0.64ns Box-wing 0.30ns
Difference to linear fit:
CODE 0.71ns Box-wing 0.32ns
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 18
ESA UNCLASSIFIED - For Official Use
Conclusions
• The evolutions in the GNSS space segments introduce challenges for modelling of spacecraft dynamics (new satellites with different characteristics, shapes weights, etc.)
• This presentation highlights the importance of GNSS satellite dynamics modelling for GNSS POD on the example of SRP impact on QZSS
• Additional evaluation of the results for GNSS satellite dynamic models can
be obtained by the characterisation of the highly accurate on-board clocks
• Independent evaluation of the GNSS satellite dynamic models can be performed via processing of SLR
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 19
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We gratefully acknowledge the excellent cooperation
with Japan Aerospace Exploration Agency
Acknowledgment
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E. Schoenemann, T. Springer, F. Dilssner, C. Garcia, C. Flohrer, F. Reichel, W. Enderle, R. Zandbergen | ESOC | 28/10/2015 | Slide 20
ESA UNCLASSIFIED - For Official Use
Thank you for your attention, please visit our web site
http://navigation-office.esa.int/