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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
Agenda ,[object Object],[object Object],[object Object],[object Object],[object Object]
Introduction of COMS (1) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
Introduction of COMS (2) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
Introduction of GOCI (1) ,[object Object],[object Object],[object Object],[object Object],[object Object]
Introduction of GOCI (2) ,[object Object],Items Technical requirements   Ground Sample Distance  (GSD)      500m    500m at the center of the target area   Target area  ,[object Object],[object Object],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
Introduction of GOCI (3) ,[object Object],(Z+ Earth) GOCI Main Unit (w/o MLI protection)
Introduction of GOCI (4) ,[object Object],GOCI Main Unit (w/o MLI protection) during integration phase
Introduction of GOCI (5) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],GOCI CMOS Detector
Introduction of GOCI (5) ,[object Object],[object Object],[object Object]
Introduction of GOCI (5) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
Introduction of GOCI (6) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
Current Status of COMS & GOCI (1) COMS launch and mission timeline
Current Status of COMS and GOCI (2) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
Current Status of COMS and GOCI (3) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
GOCI In-Orbit Performances (1) Functional chain architecture of Data Processing
GOCI In-Orbit Performances (2) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],2D mapping parameter O 2D mapping parameter F ,[object Object]
GOCI In-Orbit Performances (3) ,[object Object],[object Object],[object Object],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
GOCI In-Orbit Performances (4) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],SD image for long integration time SD image for short integration time Gain matrix
GOCI In-Orbit Performances (5) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],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, ,[object Object]
GOCI In-Orbit Performances (6) ,[object Object],[object Object],L0 image  (raw digital image, slot 7, B8) L1A image (radiance image, slot 7, B8) 08/09/2010, 00:15:00 UTC ,[object Object],where  : raw data after offset correction : Gain parameters calculated through in-orbit solar calibration
GOCI In-Orbit Performances (7) ,[object Object],[object Object],[object Object],[object Object]
GOCI In-Orbit Performances (8) ,[object Object],[object Object],[object Object],[object Object],Nominal side Redundant side
GOCI In-Orbit Performances (9) MTF ,[object Object],[object Object],[object Object]
GOCI In-Orbit Performances (10) ,[object Object],[object Object],[object Object],[object Object]
GOCI In-Orbit Performances (11) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
GOCI In-Orbit Performances (12) ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
GOCI In-Orbit Performances (13) ,[object Object],[object Object],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
GOCI In-Orbit Performances (14) ,[object Object],[object Object]
GOCI In-Orbit Performances (14) ,[object Object],[object Object]
GOCI Sample Images (1)
GOCI Sample Images (2)
GOCI Sample Images (3)
GOCI Sample Images (4)
Conclusion ,[object Object],[object Object],[object Object],[object Object]

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IGARSS 2011 pt slides_7 28 2011.ppt

Editor's Notes

  1. 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.
  2. 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.
  3. 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.
  4. 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.
  5. 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.
  6. 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.
  7. 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.
  8. 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.