OBSERVATION PERFORMANCE OF A PARIS ALTIMETER IN-ORBIT DEMONSTRATOR
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1 OBSERVATION PERFORMANCE OF A PARIS ALTIMETER IN-ORBIT DEMONSTRATOR Salvatore D Addio, Manuel Martin-Neira Acknowledgment to: Nicolas Floury, Roberto Pietro Cerdeira TEC-ETP, ETP, Electrical Engineering Department European Space Agency
2 PARIS IoD Mission Summary Table Instrument Main Scientific Product Secondary Scientific Product Scientific by-products Particular Application PARIS Altimeter Mesoscale Ocean Altimetry Polar Ice Thickness Ionospheric total electron content Wind speed over ocean Wind direction over ocean Significant Wave Height Mean Square Slope of ocean surface Sea Ice Extent Tsunami detection In-orbit Demonstrator Operational Mission Orbit Orbital Height Swath Revisit Time Spatial Resolution Antenna Diameter / Gain Number of Beams Frequencies Total Altimetry Accuracy (1) Platform Launcher Configuration Polar Sun Synchronous 800 km 900 km 3 days 100 km 0.9 m / 19 db 4 GPS L1+L5 Galileo E1+E5 < 17-0 cm PROBA-like Piggy back Polar Sun Synchronous 1500 km 1500 km days < 100 km.4 m / 30 db 16 All 3 bands of GPS, GLONASS, GALILEO, BEIDOU < cm PROTEUS-like Main passenger
3 Factors affecting altimetry accuracy Precision Accuracy Factors affecting altimetry accuracy Allowed incidence angle of specular point Instrument Characteristics: 1. Antenna Gain, Receiver NF. XC Coherent integration time Waveform Retracking Performance Uncertainties on Propagation: 1. Ionosphere. Troposphere 3. EM Bias 4. Skewness Bias Uncertainties on Geometry/Orbit Residual instrument errors after calibration Comment Higher incidence angle reduces the height precision, but increases swath Scanning reduce antenna gain 1. Improve SNR. Fundamental for performance optimization Optimum retracker to be defined 1. Use of or 3 Frequencies. Estimated or measured 3. Frequency Dependent 4. Fraction of EM Bias On-board Delay/Amplitude Calibration needed
4 PARIS IOD System Concept Direct Cross-correlation (DxR( DxR) High gain beams for direct signals (D) High gain beams for reflected signals (R) Implicit use of full GNSS bandwidth (3x40 MHz) Dual or Trial Frequency for precise estimation of ionospheric delay Precise on-board delay calibration Precise on-board amplitude calibration L5 L L1 40 MHz 40 MHz 40 MHz
5 PARIS IoD L1 Power Waveform GPS L1 Composite, Orbit Height: 500Km, Down-Looking Antenna Gain: 19dBi, Nadir Looking Geometry
6 Factors affecting altimetry accuracy Precision Accuracy Factors affecting altimetry accuracy Allowed incidence angle of specular point Instrument Characteristics: 1. Antenna Gain, Receiver NF. XC Coherent integration time Waveform Retracking Performance Uncertainties on Propagation: 1. Ionosphere. Troposphere 3. EM Bias 4. Skewness Bias Uncertainties on Geometry/Orbit Residual instrument errors after calibration Comment Higher incidence angle reduces the height precision, but increases swath Scanning reduce antenna gain 1. Improve SNR. Fundamental for performance optimization Optimum retracker to be defined 1. Use of or 3 Frequencies. Estimated or measured 3. Frequency Dependent 4. Fraction of EM Bias On-board Delay/Amplitude Calibration needed
7 Max Incidence Angle (1/) 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 G P Ionosphere i i s O
8 Max Incidence Angle (/) a) Altimetric performance degrades with incidence angle b) Ionospheric delay and antenna losses increase with incidence angle (a) dh d cosi (b) P G Antenna gain Ionosphere i i s dh i d The incidence angle i should be minimised. O
9 Factors affecting altimetry accuracy Precision Accuracy Factors affecting altimetry accuracy Allowed incidence angle of specular point Instrument Characteristics: 1. Antenna Gain, Receiver NF. XC Coherent integration time Waveform Retracking Performance Uncertainties on Propagation: 1. Ionosphere. Troposphere 3. EM Bias 4. Skewness Bias Uncertainties on Geometry/Orbit Residual instrument errors after calibration Comment Higher incidence angle reduces the height precision, but increases swath Scanning reduce antenna gain 1. Improve SNR. To be optimized for maximum precision Optimum retracker to be defined 1. Use of or 3 Frequencies. Estimated or measured 3. Frequency Dependent 4. Fraction of EM Bias On-board Delay/Amplitude Calibration needed
10 Cross-Correlation Correlation Integration Time Interferometric Processing Schematic T c Tc dt Wi N Ninc For a given target along track spatial resolution,, e.g. 100Km,, the coherent integration time and the incoherent averaging are inversely proportional: T 100Km TcNinc
11 Power Altiemtry Waveform 1 chip delay S Z P ACF, R,, sin ft ft c c
12 PARIS Flight Dir The role of Tc Low High Tc RX S Z P ACF, R,, sin ft ft c c
13 PARIS Flight Dir Tc vs SNR SNR SP RX T C ft sin SNR P ACF T c SP R,, c ft, c
14 Cross-Correlation Correlation Integration Time (Tc( Tc) Analytical model for altimetry precision: h inc, SP Z, S cpzs, cos P Ninc SNR SNR N inc T 100Km T c SNR T c h 1 1 const1 Tc 1 const T const T c c Tc shall be chosen such to have a sufficient SNR (e.g. 6dB) but cannot be increased further otherwise the altimetric precision is degraded because speckle is not averaged enough However, Tc cannot be too low otherwise consecutive XC samples may be correlated and speckle would anyway not be averaged
15 Interferometric Processing SNR Up / Down-looking Antenna Gain and Up/Down RX NF shall be such to have sufficient SNR In PARIS IoD with interferometric processing, the final power waveform SNR is given as: SNR int 1 SNR cr 1 SNR SNR D R
16 Factors affecting altimetry accuracy Precision Accuracy Factors affecting altimetry accuracy Allowed incidence angle of specular point Instrument Characteristics: 1. Antenna Gain, Receiver NF. XC Coherent integration time Waveform Retracking Performance Uncertainties on Propagation: 1. Ionosphere. Troposphere 3. EM Bias 4. Skewness Bias Uncertainties on Geometry/Orbit Residual instrument errors after calibration Comment Higher incidence angle reduces the height precision, but increases swath Scanning reduce antenna gain 1. Improve SNR. Fundamental for performance optimization Optimum retracker to be defined 1. Use of or 3 Frequencies. Estimated or measured 3. Frequency Dependent 4. Fraction of EM Bias On-board Delay/Amplitude Calibration needed
17 Waveform Retracking The retracking has the objective of estimating the sea state parameters and the sea mean surface height by fitting a theoretical model to measured waveforms Maximum likelihood estimation (MLE) or on weighted least squares estimation has been extensively used in Conventional Radar Altimetry. The MLE method estimates the parameters by determining which values maximize the probability of obtaining the recorded waveform shape e in the presence of noise of a given statistical distribution. W ( ) f,, SWH sp 0 delay SWH
18 Factors affecting altimetry accuracy Precision Accuracy Factors affecting altimetry accuracy Allowed incidence angle of specular point Instrument Characteristics: 1. Antenna Gain, Receiver NF. XC Coherent integration time Waveform Retracking Performance Uncertainties on Propagation: 1. Ionosphere. Troposphere 3. EM Bias 4. Skewness Bias Uncertainties on Geometry/Orbit Residual instrument errors after calibration Comment Higher incidence angle reduces the height precision, but increases swath Scanning reduce antenna gain 1. Improve SNR. Fundamental for performance optimization Optimum retracker to be defined 1. Use of or 3 Frequencies. Estimated or measured 3. Frequency Dependent 4. Fraction of EM Bias On-board Delay/Amplitude Calibration needed
19 The impact of Ionosphere At L-band,, the ionosphere is a major contributor to the propagation delay h cos i I with 40.3 TEC f I Multi-frequency observations allow to remove the ionospheric effect 1 hcosi 5 hcosi I f 1 I f 5 h cosi cosi 1 1 However this is at the expense of a severe error amplification factor h
20 Possible Ionospheric Correction Method Starting from range equation: Multi-frequency observations are taken: y h x f y1 1 f1 h y 1 f x 5 following uncertainties: The ionospheric delays are retrieved with the following x x y x 3. y f f1 f 1 cosi cosi 5 A regression is performed over N samples of ionospheric delay x y x y f1 N f5 N The smoothed ionospheric delay is used in the range equations, resulting in an improved error amplification factor x N I N y h h 15 f1 f5 cosif cosi cosi h N 3. 4N y for 5 (4th order regression) h y N 1.7 for 3 (linear regression) h y N
21 Ionospheric Correction: Example 1/ What matters in mesoscale ocean altimetry is the difference between the ionospheric delay at two specular points Worst case is between nadir (i=0) ) and edge of swath (i=30) G 1 G P Ionosphere i i s 1 s O
22 Ionospheric Correction: Example / Vertical Delay (m) m Derived from RA- real data m Mesoscale Delay (m) m m Residual Delay (m) m km averaging of mesoscale delay applied m
23 PARIS IoD Error Budget Parameter Instrument Noise and Speckle Ionosphere Averaging Noise Ionosphere Residual Troposphere (Wet and Dry) EM Bias Skewness Bias Orbit / Geometry Instrument error residuals Total RMS Height Accuracy IOD L1 Height Accuracy on 100Km, G=0dBi, H=800Km 1.5 cm 9.5 cm ( frequencies, N=3) 5 cm 5 cm cm 1 cm 5 cm cm 18 cm at Edge of Swath
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