IGARSS 2011 pt slides_7 28 2011.ppt

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  • Spectral band selection is ensured by a 9-position filter wheel: 8 positions correspond to the 8 wavebands, and the ninth one is used for detector dark current measurement by providing a full occultation view.
  • Spectral band selection is ensured by a 9-position filter wheel: 8 positions correspond to the 8 wavebands, and the ninth one is used for detector dark current measurement by providing a full occultation view.
  • Five Key Elements: Three mechanisms (SCM, FWM, POM), Telescope Assembly and FPA. Functional chain, in the order of: SCM, POM, Telescope Assembly, FWM, FPA Calibration mechanism: SD & Diffuser Aging Monitoring Device (DAMD), a smaller aperture diffuser using identical material to SD (QVD), to be used infrequently and suffer virtually no degradation due to contaminant buildup and polymerization from solar exposure, which allows maintaining the calibration accuracy.
  • Spectral band selection is ensured by a 9-position filter wheel: 8 positions correspond to the 8 wavebands, and the ninth one is used for detector dark current measurement by providing a full occultation view.
  • Spectral band selection is ensured by a 9-position filter wheel: 8 positions correspond to the 8 wavebands, and the ninth one is used for detector dark current measurement by providing a full occultation view.
  • Spectral band selection is ensured by a 9-position filter wheel: 8 positions correspond to the 8 wavebands, and the ninth one is used for detector dark current measurement by providing a full occultation view.
  • Spectral band selection is ensured by a 9-position filter wheel: 8 positions correspond to the 8 wavebands, and the ninth one is used for detector dark current measurement by providing a full occultation view.
  • Spectral band selection is ensured by a 9-position filter wheel: 8 positions correspond to the 8 wavebands, and the ninth one is used for detector dark current measurement by providing a full occultation view.
  • IGARSS 2011 pt slides_7 28 2011.ppt

    1. 1. GOCI: Early In-Orbit Performances Han-Dol KIM*, Gm-Sil Kang*, Joo-Hyung Ryu** Pierre Coste † , Philippe Meyer † *Korea Aerospace Research Institute (KARI) **Korea Ocean Research and Development Institute (KORDI) † EADS Astrium July 28, 2011 Vancouver, CANADA 2011 IGARSS TH3.T05
    2. 2. Agenda <ul><li>Introduction of COMS </li></ul><ul><li>Introduction of GOCI </li></ul><ul><li>Current Status of COMS and GOCI </li></ul><ul><li>GOCI In-Orbit Performances </li></ul><ul><li>Conclusion </li></ul>
    3. 3. Introduction of COMS (1) <ul><li>COMS: Communication, Ocean and Meteorological Satellite </li></ul><ul><li>Geostationary satellite </li></ul><ul><li>Mass at Launch: 2460 kg </li></ul><ul><li>Orbital Location: 128.2 o E </li></ul><ul><li>Design Life time: 10 years </li></ul><ul><li>Operational Life: 7.7 years </li></ul><ul><li>Launch: June 26, 2910, 21:41 (UTC) </li></ul><ul><li>Launcher: Ariane 5 ECA </li></ul><ul><li>COMS Missions </li></ul><ul><li>A meteo mission (MI)* </li></ul><ul><li>An ocean imager mission (GOCI)** </li></ul><ul><li>An experimental Ka band telecommunication mission </li></ul><ul><li>* MI: Meteorological Imager </li></ul><ul><li>** GOCI: Geostationary Ocean Color Imager </li></ul>
    4. 4. Introduction of COMS (2) <ul><li>The main characteristics of COMS </li></ul><ul><li>- Operational lifetime: 7.7 years </li></ul><ul><li>- Design lifetime: 10 years </li></ul><ul><li>- Orbital position: 128.2°E </li></ul><ul><li>- Launch mass: 2460 Kg </li></ul><ul><li>- Payload mass: 316 Kg </li></ul><ul><li>- Payload power: 1077 W </li></ul><ul><li>- Power generation: 2396 W by GaAs cells solar array </li></ul><ul><li>- Pointing performance: </li></ul><ul><li>* better than +/- 0.05 ° absolute pointing error in roll and pitch for </li></ul><ul><li>MI/GOCI </li></ul><ul><li>* better than 0,11 ° (half cone) error for Ka band RF beam pointing </li></ul><ul><li>* pointing stability; </li></ul><ul><li>10µrad (N/S and E/W) peak to peak over 8s period </li></ul><ul><li>55µrad (N/S and E/W) peak to peak over 120s period </li></ul>
    5. 5. Introduction of GOCI (1) <ul><li>Overview </li></ul><ul><li>world’s 1st geostationary ocean color imager, jointly developed by EADS Astrium and KARI </li></ul><ul><li>8 channels/spectral bands (6-Visible and 2-NIR) </li></ul><ul><li>provides multi-spectral data regarding coastal ocean environment for marine science research and application purpose </li></ul><ul><li>spectral band selection is ensured by a 9-position filter wheel: 8 positions correspond to the 8 wavebands (the ninth one for detector dark current measurement) </li></ul>
    6. 6. Introduction of GOCI (2) <ul><li>Performance requirement specification </li></ul>Items Technical requirements Ground Sample Distance (GSD)  500m  500m at the center of the target area Target area <ul><li>2500km  2500km </li></ul><ul><li>centered on (36  N , 130  E) </li></ul>Spectral coverage 412 nm ~ 865 nm (8 channels) Bandwidth 10 nm ~ 40 nm SNR 750 ~ 1200 System MTF 0.3 on all bands (after ground processing) Dynamic range NEdR ~ Maximum cloud radiance Radiometric calibration accuracy 4 % Digitization 12 bit
    7. 7. Introduction of GOCI (3) <ul><li>Key Design Features (i) </li></ul>(Z+ Earth) GOCI Main Unit (w/o MLI protection)
    8. 8. Introduction of GOCI (4) <ul><li>Key Design Features (ii) </li></ul>GOCI Main Unit (w/o MLI protection) during integration phase
    9. 9. Introduction of GOCI (5) <ul><li>Key Design Features (iii) </li></ul><ul><li>- FPA (Focal Plane Assembly) </li></ul><ul><li>GOCI Detector & FEE (Front End Electronics) </li></ul><ul><ul><li>2-D array, COMS detector: 1415(EW)x1432(NS) pixels </li></ul></ul><ul><ul><li>2 sub-arrays: 1415 x 715 pixels </li></ul></ul><ul><ul><li>2 lead-out channels for each sub-array </li></ul></ul><ul><ul><li>Low noise amplification of 4 lead-out channel signals of the detector by FEE </li></ul></ul>GOCI CMOS Detector
    10. 10. Introduction of GOCI (5) <ul><li>Key Design Features (vi) </li></ul><ul><li>- Telescope Assembly: </li></ul><ul><li>* Three Mirror Anastigmat (TMA) design, providing good MTF performance over the field of view on focal plane array, with all mirrors made of SiC to lower weights and minimize thermal effects </li></ul>
    11. 11. Introduction of GOCI (5) <ul><li>Key Design Features (v) </li></ul><ul><li>- FWM (Filter Wheel Mechanism) </li></ul><ul><li>* 1-D rotation, Filter Wheel </li></ul><ul><ul><li>* 8 spectral filters </li></ul></ul><ul><ul><li>* 1 Dark plate for offset measurement </li></ul></ul><ul><li>- POM (Pointing Mechanism) </li></ul><ul><li>* An High accuracy pointing assembly, used to select slot </li></ul><ul><li>positions </li></ul>
    12. 12. Introduction of GOCI (6) <ul><li>Key Design Features (vi) </li></ul><ul><li>- SCM (Shutter & Calibration Mechanism) </li></ul><ul><li>Shutter wheel (1-D rotation) </li></ul><ul><ul><li>* For the earth view when opening and for closing instrument cavity when it is inactive </li></ul></ul><ul><ul><li>* SD (Solar Diffuser): for the sun view. effectively insensitive to radiation degradation over mission life time ( made of Quasi Volumic Diffuser (QVD)) . </li></ul></ul><ul><ul><li>* DAMD (Diffuser Aging Monitoring Device): for the sun view. a smaller aperture diffuser using identical material to SD, to be used infrequently and suffer virtually no degradation, which allows maintaining the calibration accuracy. </li></ul></ul>
    13. 13. Current Status of COMS & GOCI (1) COMS launch and mission timeline
    14. 14. Current Status of COMS and GOCI (2) <ul><li>COMS lOT Summary (July 2010~ Feb 2011) </li></ul><ul><li>Bus IOT </li></ul><ul><li>- All functional checks are completed and Bus is in </li></ul><ul><li>good health. </li></ul><ul><li>- Performance checks are completed and </li></ul><ul><li>subsystems are showing excellent performances. </li></ul><ul><li>Payload IOT </li></ul><ul><li>- All functional checks are completed and all three </li></ul><ul><li>payloads are in good health. </li></ul><ul><li>- Radiometric performance checks and radiometric </li></ul><ul><li>calibration have been completed. </li></ul><ul><li>- Geometric calibration has been completed with the </li></ul><ul><li>focus on INR tuning. </li></ul>
    15. 15. Current Status of COMS and GOCI (3) <ul><li>GOCI Status Summary </li></ul><ul><li>Normal Operation for the service to the end user </li></ul><ul><li>has set forth at the completion of IOT (FAR), </li></ul><ul><li>from April 2011. </li></ul><ul><li>Current GOCI Status </li></ul><ul><li>- GOCI is in good health with all functions in good </li></ul><ul><li>check. </li></ul><ul><li>- Radiometric calibration is exhibiting good trace of </li></ul><ul><li>performance, calibration and stability. </li></ul><ul><li>- Geometric correction is exhibiting good landmark </li></ul><ul><li>matching and excellent INR performance metric. </li></ul>
    16. 16. GOCI In-Orbit Performances (1) Functional chain architecture of Data Processing
    17. 17. GOCI In-Orbit Performances (2) <ul><li>Radiometric Performances (1) </li></ul><ul><li>Radiance Response </li></ul><ul><ul><li>S: Output (Digital count), L: Incident Radiance </li></ul></ul><ul><ul><li>G: Linear gain, b: Nonlinear gain, T int : integration time </li></ul></ul><ul><ul><li>O: Dark current offset parameter, F: Fixed offset parameter </li></ul></ul><ul><ul><li>GOCI radiometric model has been validated through ground test </li></ul></ul>2D mapping parameter O 2D mapping parameter F <ul><ul><li>In orbit offset parameter  Ground offset parameter </li></ul></ul>
    18. 18. GOCI In-Orbit Performances (3) <ul><li>Radiometric Performances (2) </li></ul><ul><li>Radiance Response (ii) </li></ul><ul><ul><li>GOCI radiometric model has been validated through ground test </li></ul></ul>Ground Measured Radiometric Response In-orbit radiometric responsivity G & b , PRNU (Pixel Response Non-Uniformity)  On-ground measured values Digital count image of Sun diffused by SD
    19. 19. GOCI In-Orbit Performances (4) <ul><li>Radiometric Performances (3) </li></ul><ul><li>Radiometric calibration and stability (i) </li></ul><ul><li>GOCI radiometric calibration using Sun light through Solar diffuser </li></ul><ul><li> Covering whole imaging chain (telescope and video chain) for Earth </li></ul><ul><li>observation (SD is located in front of pointing mirror) </li></ul><ul><li> Covering full pupil </li></ul><ul><li> Monitoring of Solar diffuser aging using secondary solar diffuser </li></ul><ul><ul><li>In orbit calibration method using two images has been verified through IOT duration. </li></ul></ul>SD image for long integration time SD image for short integration time Gain matrix
    20. 20. GOCI In-Orbit Performances (5) <ul><li>Radiometric Performances (4) </li></ul><ul><li>Radiometric calibration and stability (ii) </li></ul><ul><ul><li>Using two measurement points S A , S B (two images) </li></ul></ul><ul><ul><li>: image with long integration time & image with short integration time </li></ul></ul><ul><ul><li>Using solar irradiance E S calculated from the solar spectrum model (Thuillier 2004) provided by GOCI user group </li></ul></ul><ul><ul><li>Using diffusion model  SD of SD characterized on-ground </li></ul></ul><ul><ul><li>Using solar incident angle  SD calculated from Ephemeris data and telemetry </li></ul></ul>Linear gain Non-linear gain : sun images : measurement parameter for sun imaging  SD: diffusion factor of SD,  SD : solar incident angle, T SD : integration time where E s : solar irradiance, <ul><li>Gain matrix calculation </li></ul>
    21. 21. GOCI In-Orbit Performances (6) <ul><li>Radiometric Performances (5) </li></ul><ul><li>Radiometric calibration and stability (iii) </li></ul>L0 image (raw digital image, slot 7, B8) L1A image (radiance image, slot 7, B8) 08/09/2010, 00:15:00 UTC <ul><ul><li>Radiance image calculation using in-orbit gain matrix </li></ul></ul>where : raw data after offset correction : Gain parameters calculated through in-orbit solar calibration
    22. 22. GOCI In-Orbit Performances (7) <ul><li>Radiometric Performances (6) </li></ul><ul><li>Radiometric calibration and stability (iv) </li></ul><ul><ul><li>Evolution of mean gain over 5 months: about 2% degradation </li></ul></ul><ul><ul><li>(Stabilization after 3 months) </li></ul></ul>
    23. 23. GOCI In-Orbit Performances (8) <ul><li>Radiometric Performances (7) </li></ul><ul><li>SNR </li></ul><ul><ul><li>SNR has been assessed indirectly by using in orbit gain matrix. </li></ul></ul><ul><ul><li>IOT SNR measurement > Specification </li></ul></ul>Nominal side Redundant side
    24. 24. GOCI In-Orbit Performances (9) MTF <ul><ul><li>MTF has been assessed by KEF image for Band 7 and Ban 8. </li></ul></ul><ul><ul><li>IOT MTF measurement > Specification </li></ul></ul><ul><ul><li>Example of E/W MTF measurement (KEF) </li></ul></ul>
    25. 25. GOCI In-Orbit Performances (10) <ul><li>Geometric Performances (1) </li></ul><ul><li>GSD </li></ul><ul><ul><li>GSD at FOV center has been assessed. </li></ul></ul><ul><ul><li>IOT GSD measurement: OK </li></ul></ul>
    26. 26. GOCI In-Orbit Performances (11) <ul><li>Geometric Performances (2) </li></ul><ul><li>Geometric Correction: INR </li></ul><ul><li>- A new, noble approach to INR system design </li></ul><ul><li>- Not directly dependent on system and/or payload </li></ul><ul><li>models and hence can avoid any indispensible </li></ul><ul><li>modeling and/or prediction error in the process </li></ul><ul><li>- Acquisition of sufficient number of landmarks in </li></ul><ul><li>good quality is key to this design </li></ul><ul><li>- Excellent landmark matching algorithm and the </li></ul><ul><li>fine-tuning of newly established landmark database </li></ul><ul><li>with ample landmark sites render such acquisition </li></ul><ul><li>of sufficient number of good landmarks </li></ul>
    27. 27. GOCI In-Orbit Performances (12) <ul><li>Geometric Performances (3) </li></ul><ul><li>GOCI INR performances (i) </li></ul><ul><li>- Accuracy performances on landmarks have been checked </li></ul><ul><li>on KORDI GOCI operational platform (1FEB2011 to 7FEB2011) </li></ul><ul><li>- GOCI INR performances have been re-checked after the </li></ul><ul><li>final adjustment (15FEB2011 to 21FEB2011) </li></ul>
    28. 28. GOCI In-Orbit Performances (13) <ul><li>Geometric Performances (4) </li></ul><ul><li>GOCI INR performances (ii) </li></ul>Mean Standard Deviation Performance Performance (  rad) EW NS EW NS EW NS EW NS Navigation 0.05 0.46 0.56 0.52 1.72 2.03 24.1 28.4 Band-to-Band Reg. -0.01 0.00 0.30 0.25 0.92 0.74 12.9 10.4
    29. 29. GOCI In-Orbit Performances (14) <ul><li>Geometric Performances (5) </li></ul><ul><li>GOCI INR performances (iii): Example of shoreline matching (B7) </li></ul>
    30. 30. GOCI In-Orbit Performances (14) <ul><li>Geometric Performances (6) </li></ul><ul><li>GOCI INR performances (vi): Example of shoreline matching (B7) </li></ul>
    31. 31. GOCI Sample Images (1)
    32. 32. GOCI Sample Images (2)
    33. 33. GOCI Sample Images (3)
    34. 34. GOCI Sample Images (4)
    35. 35. Conclusion <ul><li>The newly developed GOCI is demonstrating quite decent performances in orbit, both in radiometric and geometric aspects. </li></ul><ul><li>It is anticipated that such GOCI image data will bring a new dimension to the geostationary remote sensing and in the related scientific research fields. </li></ul><ul><li>More in-depth review, thorough analysis and active iteration are desired to define the requirement specification for the next generation GOCI (‘GOCI-2’). </li></ul><ul><li>It is hoped that GOCI will further be expanded in terms of its design, development, operation and applications, into the next generation of geostationary remote sensing satellites. </li></ul>

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