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END-TO-END PERFORMANCE ANALYSIS OF THE  PARIS IN-ORBIT DEMONSTRATOR  OCEAN ALTIMETER Salvatore D’Addio,  Manuel Martin-Neira , Chris Buck Acknowledgment: Nicolas Floury, Roberto Pietro Cerdeira TEC-ETP, Electrical Engineering Department European Space Agency
The PARIS Concept ,[object Object],[object Object]
PARIS IOD Key Features ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],L1 L5 L2 40 MHz 40 MHz 40 MHz
PARIS IoD L1 Power Waveform ,[object Object]
PARIS IoD Mission Summary Table Main passenger Piggy back Launcher Configuration PROTEUS-like PROBA-like Platform < 5-7.5 cm < 17-20 cm Total Altimetry Accuracy (1  ) All 3 bands of GPS, GLONASS, GALILEO, BEIDOU GPS L1+L5  Galileo E1+E5 Frequencies 16 4 Number of Beams 2.4 m / 30 dB 0.9 m / 19 dB Antenna Diameter / Gain < 100 km 100 km Spatial Resolution 2 days 3 days Revisit Time 1500 km 900 km Swath 1500 km 800 km Orbital Height Polar Sun Synchronous Polar Sun Synchronous Orbit  Operational Mission In-orbit Demonstrator Tsunami detection Particular Application Ionospheric total electron content Wind speed and wind direction over ocean Significant Wave Height Mean Square Slope of ocean surface Sea Ice Extent River  and lake water level Scientific by-products Polar Ice Thickness Secondary Scientific Product Mesoscale Ocean Altimetry Main Scientific Product PARIS Altimeter Instrument
Factors affecting altimetry performance On-board Delay/Amplitude Calibration needed  Residual instrument errors after calibration Uncertainties on Geometry/Orbit ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Accuracy Optimum retracker to be defined Waveform Retracking Performance ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Allowed incidence angle  of specular point Precision Comment Factors affecting altimetry performance
Max Incidence Angle (1/2) The incidence angle plays an important role in the definition of critical parameters of the PARIS mission, such as: (a) Precision (b) Sampling and Coverage P G O s Ionosphere i i
Max Incidence Angle (2/2) a) Altimetric performance degrades with incidence angle b) Ionospheric delay and antenna loss increase with incidence angle The incidence angle should be restricted (<35  ). Coverage and sampling obtained by raising orbital height.  (a ) (b) i Antenna gain P G O s Ionosphere i i
Factors affecting altimetry performance On-board Delay/Amplitude Calibration needed  Residual instrument errors after calibration Uncertainties on Geometry/Orbit ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Accuracy Optimum retracker to be defined Waveform Retracking Performance ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Allowed incidence angle of specular point Precision Comment Factors affecting altimetry performance
Interferometric Processing SNR ,[object Object],[object Object]
Cross-Correlation Integration Time (Tc) Interferometric Processing Schematic For a given target along track spatial resolution, e.g.  100Km , the coherent integration time and the incoherent averaging are  inversely proportional :  Tc Ninc
Cross-Correlation Integration Time (Tc) 1 chip delay
Cross-Correlation Integration Time (Tc) Low Tc High Tc
Cross-Correlation Integration Time (Tc) SNR SP T C
Cross-Correlation Integration Time (Tc) ,[object Object],[object Object],[object Object]
Factors affecting altimetry performance On-board Delay/Amplitude Calibration needed  Residual instrument errors after calibration Uncertainties on Geometry/Orbit ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Accuracy Optimum retracker to be defined Waveform Retracking Performance ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Allowed incidence angle of specular point Precision Comment Factors affecting altimetry performance
Waveform Retracking ,[object Object],[object Object],[object Object],SWH delay
Factors affecting altimetry performance On-board Delay/Amplitude Calibration needed  Residual instrument errors after calibration Uncertainties on Geometry/Orbit ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Accuracy Optimum retracker to be defined Waveform Retracking Performance ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Allowed incidence angle of specular point Precision Comment Factors affecting altimetry performance
The impact of Ionosphere ,[object Object],with ,[object Object],[object Object]
Possible Ionospheric Correction Method  ,[object Object],[object Object],[object Object],[object Object],[object Object]
Ionospheric Correction: Example 1/2 ,[object Object],P G 2 O s 2 Ionosphere i i G 1 s 1
Ionospheric Correction: Example 2/2 Vertical Delay (m) Mesoscale Delay (m) Residual Delay (m) 200 km averaging of mesoscale delay applied  0.15 m +0.15 m +6 m  10 m +12 m 0 m Derived from RA-2 real data
PARIS IoD Preliminary Error Budget 5 cm Troposphere (Wet and Dry) 2 cm EM Bias 1 cm Skewness Bias 5 cm Orbit / Geometry 2 cm Instrument error residuals Ionosphere Residual Total RMS Height Accuracy Instrument Noise and Speckle Ionosphere Averaging Noise 18 cm at Edge of Swath 5 cm 9.5 cm (2 frequencies, N=3) 12.5 cm IOD Height Total Accuracy on  100Km, G=20dBi, H=800Km Parameter
CONCLUSIONS ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]

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FR4.TO5.5.ppt

  • 1. END-TO-END PERFORMANCE ANALYSIS OF THE PARIS IN-ORBIT DEMONSTRATOR OCEAN ALTIMETER Salvatore D’Addio, Manuel Martin-Neira , Chris Buck Acknowledgment: Nicolas Floury, Roberto Pietro Cerdeira TEC-ETP, Electrical Engineering Department European Space Agency
  • 2.
  • 3.
  • 4.
  • 5. PARIS IoD Mission Summary Table Main passenger Piggy back Launcher Configuration PROTEUS-like PROBA-like Platform < 5-7.5 cm < 17-20 cm Total Altimetry Accuracy (1  ) All 3 bands of GPS, GLONASS, GALILEO, BEIDOU GPS L1+L5 Galileo E1+E5 Frequencies 16 4 Number of Beams 2.4 m / 30 dB 0.9 m / 19 dB Antenna Diameter / Gain < 100 km 100 km Spatial Resolution 2 days 3 days Revisit Time 1500 km 900 km Swath 1500 km 800 km Orbital Height Polar Sun Synchronous Polar Sun Synchronous Orbit Operational Mission In-orbit Demonstrator Tsunami detection Particular Application Ionospheric total electron content Wind speed and wind direction over ocean Significant Wave Height Mean Square Slope of ocean surface Sea Ice Extent River and lake water level Scientific by-products Polar Ice Thickness Secondary Scientific Product Mesoscale Ocean Altimetry Main Scientific Product PARIS Altimeter Instrument
  • 6.
  • 7. Max Incidence Angle (1/2) The incidence angle plays an important role in the definition of critical parameters of the PARIS mission, such as: (a) Precision (b) Sampling and Coverage P G O s Ionosphere i i
  • 8. Max Incidence Angle (2/2) a) Altimetric performance degrades with incidence angle b) Ionospheric delay and antenna loss increase with incidence angle The incidence angle should be restricted (<35  ). Coverage and sampling obtained by raising orbital height. (a ) (b) i Antenna gain P G O s Ionosphere i i
  • 9.
  • 10.
  • 11. Cross-Correlation Integration Time (Tc) Interferometric Processing Schematic For a given target along track spatial resolution, e.g. 100Km , the coherent integration time and the incoherent averaging are inversely proportional : Tc Ninc
  • 13. Cross-Correlation Integration Time (Tc) Low Tc High Tc
  • 15.
  • 16.
  • 17.
  • 18.
  • 19.
  • 20.
  • 21.
  • 22. Ionospheric Correction: Example 2/2 Vertical Delay (m) Mesoscale Delay (m) Residual Delay (m) 200 km averaging of mesoscale delay applied  0.15 m +0.15 m +6 m  10 m +12 m 0 m Derived from RA-2 real data
  • 23. PARIS IoD Preliminary Error Budget 5 cm Troposphere (Wet and Dry) 2 cm EM Bias 1 cm Skewness Bias 5 cm Orbit / Geometry 2 cm Instrument error residuals Ionosphere Residual Total RMS Height Accuracy Instrument Noise and Speckle Ionosphere Averaging Noise 18 cm at Edge of Swath 5 cm 9.5 cm (2 frequencies, N=3) 12.5 cm IOD Height Total Accuracy on 100Km, G=20dBi, H=800Km Parameter
  • 24.