Kazuhiro TANAKA GCOM project team/jaxa April, 2016

Transcription

1 Kazuhiro TANAKA GCOM project team/jaxa April, SPIE Asia-Pacific 216 at New Dehli, India 1

2 GCOM mission and satellites SGLI specification and IRS overview Current Status IRS Proto Flight Test Verification Flow Verification Matrix Early Test Results Geometric Performance Test Radiometric Performance Test for Shortwave Infrared Channels Radiometric Peformance Test for Thermal Infrared Channels Spectral Response Conclusion SPIE Asia-Pacfic 216, New Dehli, India 2

3 Global observation satellite system as JAXA s GEOSS contribution. 2 satellite series for 5 years, total 13 years observation. GCOM-W Microwave radiometric observation for WATER CYCLE using AMSR2 (AMSR-E follow on) GCOM-C Optical multi-channel observation for RADIATION BUDGET and CARBON CYCLE using SGLI (GLI follow on) GCOM-W (WATER) AMSR2 GCOM-C (CLIMATE) GCOM-W SHIZUKU was launched on May 18, 212. GCOM-C is scheduled for launch in 217. SGLI Sensor Advanced Microwave Radiometer 2 (AMSR2) Passive Microwave Observation Water vapor, soil moisture etc Sensor Second Generation Global Imager (SGLI) Optical Observation 38nm 12 micron Cloud, Aerosol, Vegetation, Chrolophl etc SPIE Asia-Pacfic 216, New Dehli, India 3

4 Second generation Global Imager (SGLI) on GCOM-C satellite SGLI IRS ELU SGLI VNR ELU +Y deep space +X flight direction + Z earth SGLI VNR SRU SGLI IRS SRU Mission Life > 5 years Solar Paddle Mass > 4w (End of Life) about 2,kg SGLI VNR IRS SRU ELU Second Generation Global Imager Visible and Near Infrared Radiometer Infrared Scanning Radiometer Scanning Radiometer Unit Electronic Unit SPIE Asia-Pacfic 216, New Dehli, India 4

5 SGLI Specification The SGLI features are 25m spatial resolution (VNR-NP, SW3 & TIR) and polarization/along-track slant view channels (VNR-PL), which will improve land, coastal, and aerosol observations. GCOM-C SGLI characteristics Sun-synchronous Orbit (descending local time: 1:3) Altitude 798km, Inclination 98.6deg Mission Life 5 years (3 satellites; total 13 years) Push-broom electric scan (VNR) Scan Wisk-broom mechanical scan (IRS) 115km cross track (VNR: NP & PL) Scan width 14km cross track (IRS: SWI & TIR) Digitalization 12bits Polarization 3 polarization angles for PL Along track Nadir for NP, SWI and TIR, direction +45 deg and -45 deg for PL On-board calibration Multi-angle obs. for 674nm and 869nm VN: Solar diffuser, LED, Lunar cal maneuvers, and dark current by masked pixels and nighttime obs. SWI: Solar diffuser, LED, Lunar, and dark current by deep space window TIR: Black body and back ground by deep space window 25m over the Land or coastal area, and 1km over offshore SGLI channels λ Δλ L std L max NP,PL,SWI: IFOV NP, PL, SWI: SNR at Lstd CH NP, PL, SWI: nm W/m TIR: NEΔT TIR: μm /sr/μm TIR: Kelvin at 3K m VN VN VN VN VN VN VN VN VN /1 VN VN PL PL SW SW SW /1 SW T /1 T /1 SPIE Asia-Pacfic 216, New Dehli, India 5

6 Infrared Scanning Radiometer (SGLI-IRS) Earth 1.4m Flight direction OBS Light Engineering model of SGLI-IRS for vibration test configuration.6m SWI-DET SCAN MOTOR Sterling Cooler BLACK BODY Optical Bench Weight: 193kg Power: 4W TIR-DET SPIE Asia-Pacfic 216, New Dehli, India 6

7 Current Status SGLI consists of two sensors, SGLI-VNR and SGLI-IRS IRS sensor system manufacturing and integration were finished. The sensor level pre-flight tests started in December 214. IRStestisinthefinalstagebeforethedelivery to the satellite system. Satellite level test will start within 216 and planned for launch in 217. SPIE Asia-Pacfic 216, New Dehli, India 7

8 March 17, 216 at TSKUBA Compatibility test with satellite system SGLI VNR SGLI IRS Flight direction SPIE Asia-Pacfic 216, New Dehli, India 8

9 Initial Geometry Test Initial Integrating Sphere Solar Direction Dependence ELU-SRU I/F Test Thermal Vacuum Test NOW Dec. 214 March 215 April 215 August 215 November 215 March 216 Satellite I/F Test EMC Test May 216 June 216 July 216 Vibration Acoustic Excitation Final Integrating Sphere Final Geometry Test TIR Radiometry Environment Test Campaign Dynamic Range / Background NEdT Linearity Detector Uniformity Detector Temperature BlackBody Comparison Initial SWI Radiometry Dynamic Range Detector Uniformity SNR Stability (Dark, Signal) Linearity Onboard Calibrator (Halogen, LED) Final SWI Radiometry Initial TIR Health Check BlackBody Initial IRS Geometry FOV, IFOV Alignment Scanning Perfomance MTF Registration Comparison Comparison Final TIR Health Check Final IRS Geometry Integration Sphere SWI Radiometry TIR Radiometry IRS Geometry IRS-SRU Space BlackBody TempControled BlackBody IRS-SRU Colimeter IRS-SRU Rotation Stage SPIE Asia-Pacfic 216, New Dehli, India 9

10 Component Test & Integration Initial Electric Performance Test (I-EPT) Thermal Vaccum Test (TVT) EMC Test Vibration Acoustice Excitation Final Electric Performance Test (F-EPT) Geometry FOV, IFOV Component Rotation Table Rotation Table MTF Component Rotation Table Rotation Table Alignment Integration Rotation Table Cube Mirror - Cube Mirror Rotation Table Scanning Perfomance Component Rotation Table Resolver Resolver Resolver Rotation Table Registration Component Rotation Table Rotation Table SWI Radiometry Dynamic Range Component Integrating Sphere Integrating Sphere SNR Component Integrating Sphere Integrating Sphere Linearity Component Integrating Sphere Integrating Sphere Detector Uniformity Component Integrating Sphere Integrating Sphere Stability (Dark, Signal) Component Integrating Sphere Integrating Sphere Onboard Calibrator (Halogen) Component Calibrator Test Calibrator Test Calibrator Test Calibrator Test Calibrator Test Onboard Calibrator (LED) Component Calibrator Test Calibrator Test Calibrator Test Calibrator Test Calibrator Test Onboard Calibrator (Light Guide) Component Angle Dependence TIR Radiometry Dynamic Range / Background Component - TVT Test NEdT Component Black Body TVT Test Black Body Black Body Black Body Linearity Component - TVT Test Detector Uniformity Component Black Body TVT Test Black Body Black Body Black Body Detector Temperature Component Ambient Test TVT Test Ambient Test Ambient Test Ambient Test BlackBody (On-Board) Component Ambient Test TVT Test Ambient Test Ambient Test Ambient Test BlackBody (Ambient) Component Ambient BBC / LN2 - Ambient BBC Ambient BBC Ambient BBC BlackBody (TVT) - - TVT Test SPIE Asia-Pacfic 216, New Dehli, India 1

11 Objectives to confirm that IRS was integrated mechanically as designed to obtain the geometry data processing parameters after the launch detector position and alignment is measured rotation stage (3 rotation axis, 2 linear translation) collimator (halogen lamp for shortwave IR, black body for thermal IR) Test results : MTF >.35 req. detector position <.2 pixel (25m) accuracy AT Pixel [25m] CT Pixel [25m] TIR-1 req TIR-2 req TIR-1 meas. TIR-2 meas. SWI-2 req SWI-4 req SWI-2 meas SWI-4 meas. MTF [@Nyquist Freq.] MTF Defocus Curve (IRS SWIR) MTF spec.=.35 SW2 AT SW2 CT SW4 AT SW4 CT Defocus Position [mm] SPIE Asia-Pacfic 216, New Dehli, India 11

12 Objectives to confirm that IRS/SWI was integrated radiometrically as designed to obtain the gain parameter for the data processing Traceable to the Japanese national standard Gold coated integrated sphere developed by JAXA s sensor group Calibrated with fixed point black body Test results : all requirements met. Small offset non-linearity in high temperature ; under study The humidity effects in 1.36micron channels ; under study. Signal Level (min) Gain Noise Band λc Lmax Lstd Saturation Gain Linearity Error (max) Sigma (max) SNR Ch Width Dark Radiance Corrected Radiance Corrected (495DN) (min) Lstd Worst Lmax Lstd Dark Lstd Spec. [micron] [nm] [W*] [DN] [W*] [DN] [DN] [W*] [W*/DN] [%] [DN] [DN] [DN] [DN] (min) SWI % SWI % SWI % SWI % [W*] = [W/m2/str/µm] SPIE Asia-Pacfic 216, New Dehli, India 12

13 2 15 SWI-1 : 1.5micron 2 15 SWI-2 : 1.39micron 2 15 SWI-3 : 1.63micron 2 15 SWI-4 : 2.21micron Linearity Error [DN] Linearity Error [DN] Linearity Error [DN] Linearity Error [DN] [W/m^w/str/micron] [W/m^w/str/micron] [W/m^w/str/micron] [W/m^w/str/micron] req. [DN] Pixel-1 Pixel-2 req. [DN] Pixel-1 Pixel-2 req. [DN] Pixel-1 Pixel-2 req. [DN] Pixel-1 Pixel-2 Pixel-3 Pixel-4 Pixel-5 Pixel-3 Pixel-4 Pixel-5 Pixel-3 Pixel-4 Pixel-5 Pixel-3 Pixel-4 Pixel-5 Linearity Error [%] 3.% 2.5% 2.% 1.5% 1.%.5%.% -.5% -1.% -1.5% -2.% -2.5% -3.% SWI [W/m^w/str/micron] Linearity Error [%] 3.% 2.5% 2.% 1.5% 1.%.5%.% -.5% -1.% -1.5% -2.% -2.5% -3.% SWI [W/m^w/str/micron] Linearity Error [%] 3.% 2.5% 2.% 1.5% 1.%.5%.% -.5% -1.% -1.5% -2.% -2.5% -3.% SWI [W/m^w/str/micron] Linearity Error [%] 3.% 2.5% 2.% 1.5% 1.%.5%.% -.5% -1.% -1.5% -2.% -2.5% -3.% SWI [W/m^w/str/micron] req. [%] Pixel-1 Pixel-2 req. [%] Pixel-1 Pixel-2 req. [%] Pixel-1 Pixel-2 req. [%] Pixel-1 Pixel-2 Pixel-3 Pixel-4 Pixel-5 Pixel-3 Pixel-4 Pixel-5 Pixel-3 Pixel-4 Pixel-5 Pixel-3 Pixel-4 Pixel-5 SPIE Asia-Pacfic 216, New Dehli, India 13

14 a. 1.6μm LED with temperature correction for the absolute reference b. Halogen color temperature and emissivity estimation from the lab. data c. Relative and absolute calibration for all 4 channels d. Total calibration error is estimated as 1.6 to 4.3 % (1σ;preliminary) Normalized Radiance Color temperature Wave length [nm] 26 22b b Lamp Data Color Temp [K] b. 24 LED Temp a. 23 Dependence [μw] Lamp Volt [V] degree C SPIE Asia-Pacfic 216, New Dehli, India 14

15 Objectives to confirm that IRS/TIR was integrated radiometrically as designed. to obtain the gain parameter Specially designed black body for the thermal vacuum environment Test results : under calculation σ temp <.1K Temp Stability <.1K ε witness >.97 Ch TIR-1 λc [micron] Band Width TIR Signal Level (min) Back Gain Noise Tmax Tstd Saturation Ground Gain Error (worst) Sigma (max) NEdT [K] Radiance Corrected Radiance Corrected (495DN) (max) 3K Tstd Worst Tmax Tstd Space Tstd Spec. [K] [DN] [K] [DN] [34K] [DN] [K/DN] [%] [%] [DN] [DN] [DN] (max) (5m) % % 1.89% % % -.88% % % -1.99% % % -1.97% m resolution, TDI = YES, Upper = BOL(COLD) / Lower = EOL(HOT) SPIE Asia-Pacfic 216, New Dehli, India 15

16 Linearity Error [DN] Linearity Error [%] TIR-11.8μm Linearity Error [DN] On-Board BBC K 22K 27K 32K 3% 2% 1% % -1% -2% TIR-11.8μm Linearity Error [%] -3% 17K 22K 27K 32K Pix1 Pix2 Pix3 Pix4 Pix5 Pix6 Pix7 Pix8 Pix9 Pix1 Pix11 Pix12 Pix13 Pix14 Pix15 Pix16 Pix17 Pix18 Pix19 Pix2 On-Board BBC Linearity Error [DN] Linearity Error [%] TIR-2 12.μm Linearity Error [DN] K 22K 27K 32K 3% 2% 1% % -1% -2% TIR-2 12.μm Linearity Error [%] -3% 17K 22K 27K 32K Pix1 Pix2 Pix3 Pix4 Pix5 Pix6 Pix7 Pix8 Pix9 Pix1 Pix11 Pix12 Pix13 Pix14 Pix15 Pix16 Pix17 Pix18 Pix19 Pix2 On-Board BBC SPIE Asia-Pacfic 216, New Dehli, India 16

17 Total Response [ma/w] Total Response [ma/w] Center Wavelength SW1 SW3 [nm] [nm] FWHM Spectral Response [nm] Half Response Lower Wavelength Total Response [ma/w] Total Response [ma/w] Upper Wavelength SW SW4 [nm] [nm] Band width Center Wavelength [nm] Weighted Spectral Response [nm] Half Response Lower Wavelength Upper Wavelength Band width SWI-1 1, ,44.4 1, , ,43.9 1, SWI-2 1, , , , , , SWI-3 1, , , , , , SWI-4 2, , , , , , TIR-1 1, , , , , , TIR-2 11, , , , , , Normalized spectral response Normalized spectral response TIR-1 TIR [nm] SPIE Asia-Pacfic 216, New Dehli, India 17

18 SGLI consists of two sensors, SGLI-VNR and SGLI-IRS IRS sensor system manufacturing and integration were finished. The sensor level pre-flight tests started in December 214. IRStestisinthefinalstagebeforethe delivery to the satellite system. Satellite level test will start in 216 and planned for launch in 217. SPIE Asia-Pacfic 216, New Dehli, India 18