17 November 2012 14 February 2009 Planned Risk Reduction Efforts for CLARREO's IR Prototype Instrument, the ARI (Absolute Radiance Interferometer) Hank Revercomb, F. A. Best, J. K. Taylor, P. J. Gero, D. C. Tobin, R. O. Knuteson, D. Adler, C. Pettersen, M. Mulligan, J. Wong, M. Schwarz, & D. Thielman University of Wisconsin-Madison ARI IR Prototype Space Science and Engineering Center CLARREO Science Definition Team Meeting National Institute of Aerospace, 30 November 2016 2016 CLARREO ARI Talks 10th SPIE Asia-Pacific Remote Sensing Symposium New Delhi, India, 5 April 2016 [Hank, paper available] 2016 International Radiation Symposium Auckland, New Zealand, 21 April 2016 [Hank Part 1, Fred Best Part 2] AMS Satellite Conference Madison, Wisconsin, 16 August 2016 – Overview and flight opportunities [Hank Part-1] – New technologies for on-orbit verification and test [Fred Best Part-2] CALCON, USU, Logan, Utah, 25 August 2016 [Fred Best] ] – The Infrared ARI Pathfinder for CLARREO EUMETSAT Meteorological Satellite Conference Darmstadt, Germany, 28 September 2016 [Hank] – Climate Benchmark quality IR measurements for CLARREO: … OSA FTS and HISE Leipzig, Germany, 28 November 2016 [Joe Taylor, FTU3C4] – The Absolute Radiance Interferometer (ARI) for the CLARREO Pathfinder: … Slide 2 Summary and Outline Introduction Instrument Overview Results Conclusion UW-SSEC Absolute Radiance Interferometer (ARI) 3.7-50 m, 4-port Calibrated FTS Pathfinder Prototype Fore-optics (“Side View”) Optics overlaid on solid model (“Top View”) Input Port B Reference FIR Detector Assembly Fore-optics AS IR Detector Assembly M1 M2 FS M4 Cooler • Pupil at cube-corner apex and near halo • Field Stop image at M2 FIR aft-optics IR aft-optics ABB/Bomem Generic Interferometer for Climate Studies (GICS) From Taylor, et al., 2016 The UW-SSEC ARI: Demonstrated Radiometric Performance (FW3A.3 – OSA FTS 2015) 15-November-2015 3 Summary and Outline Introduction Instrument Overview Results Conclusion UW-SSEC Absolute Radiance Interferometer Photos On-orbit Verification & Test System* Hot BB On-orbit Absolute Radiance Standard (OARS) and Halo Ambient BB Scene Selection Motor Scene View * Shown without integrating sphere Dashed line indicates OVTS enclosure envelope. From Taylor, et al., 2016 The UW-SSEC ARI: Demonstrated Radiometric Performance (FW3A.3 – OSA FTS 2015) 15-November-2015 4 0.2 Summary and Outline Introduction Instrument Overview Results Conclusion 313 BT Diff [K] 0 Demonstration of Required Radiometric Accuracy with IR Spectometer −0.2 2015 Data Collect – Dry Air Purge 0.2 Calibrated FTS – On-orbit Verification System Brightness Temperature 0 FIR ARI Calibration Verification Summary −1 Measured − Predicted Residual BT (Rolling Window Cal), 50.0 cm bins 0.2 −0.2 0 −0.2 0.2 LW ARI Calibration Verification Summary −1 Measured − Predicted Residual BT (Rolling Window Cal), 5.0 cm bins ±0.25K 0.2 333.04K 333 K 0.2 15 micron CO2 band 0 0.2 313.14K 333.04K 0 −0.2 272 15 micron CO2 band 313.14K 313 K 0 −0.2 0 292 −0.2 −0.2 0.2 BT Diff [K] BT Diff [K] 0.2 292.57K 0 0 −0.2 −0.2 243 0.2 253.16K 253.16K 253 K 0 750 700 650 −0.2 −0.2 0.2 243 K 400 Enhance for flight 600 800 1000 wavenumber (cm−1) 1200 800 850 900 wavenumber (cm−1) 950 1000 0.2 243.17K 0 −0.2 200 272.91K −0.2 −0.2 600 0 Cooled MCT 273 K 0 0 0.2 −0.2 0.2 272.91K 0.2 0 253 292.57K 293 K 0 −0.2 Pyroelectric 0.2 0.2 1400 243.17K 0 −0.2 600 650 700 Vacuum testing to 216 K not shown Obs − Pred after Taylor, et al., 2016 1050 750 800 850 900 wavenumber (cm−1) Combined RU 950 1000 1050 1100 ± 0.1K TRL6 ARI: 1st and only sensor to demonstrate CLARREO required performance Obs − Pred Combined RU ± 0.1K The UW-SSEC ARI: Demonstrated Radiometric Performance (FW3A.3 – OSA FTS 2015) Obs − Pred 15-November-2015 Combined RU ± 0.1K 5 Topics 1. Planned ARI Risk Reduction 2. IR Pathfinder on ISS 6 1. Planned ARI Risk Reduction Enhance blackbody Cavity Emissivity in FarIR Blackbody Cavity Heated Halo CFTS Sensor Integrate Quantum Cascade Laser (QCL) into ARI Prototype 7 ARI Front-End Key Elements OARS (On-orbit Absolute Radiance Standard) ABB (Ambient Blackbody) IS (Integrating Sphere) Scene Mirror 8 Calibrated FTS: Earth View 9 Calibrated FTS: Space Calibration View 10 OVTS: Space-2 View Used to characterize polarization* *Instrument design provides Earth viewing immunity to polarization 11 Calibrated FTS: Ambient Blackbody (ABB) FarIR emissivity to be enhanced 12 OVTS: Variable Temperature OARS View (On-orbit Verification and Test System) Controllable to a wide range of temperatures to verify absolute radiance and instrument linearity FarIR emissivity to be enhanced 13 OVTS: Thermistor Temperature Calibration The OARS has miniature phase change cells containing Ga, H2O, and Hg, used for periodic temperature calibration at 30, 0, and -38 C 14 OVTS: OARS Spectral Emissivity – Heated Halo The Heated Halo is used periodically for measuring the blackbody cavity spectral emissivity 15 OVTS: OARS Spectral Emissivity – Heated Halo Carbon nano tubes or (ARI blackbodies used undoped Z306 paint) 200-400 cm-1 emissivity to be greatly enhanced 16 Enhance blackbody Emissivity in FarIR (1) NASA LaRC had success doping Aeroglaze Z306 black paint (flat samples) with Carbon Nano particles to significantly enhance emissivity out to 60 m (Lorenzi et al. 2011). Following this approach we will establish procedures to paint and test samples and blackbody cavities, and to demonstrate performance in the CLARREO IR Instrument. • Fabricate paint witness samples and fixtures (to hold them, mimicking the cavity cone geometry) • Characterize the wet paint viscosity and dry paint thickness relationship • Prepare and spray paint cavities, and witness samples (graphene-doped paint with controlled humidity cure) • Evaluate the witness samples: Determine paint density, paint thickness, peel resistance, spectral emissivity out to 50 microns, angular dependence of emissivity, take photo micrographs to evaluate structure, measure thermal conductivity 17 Enhance blackbody Emissivity in FarIR (2) • Evaluate the cavity emissivity: Populate the cavity with thermistors and heaters, and integrate into an OARS assembly. Conduct the UW-developed Heated Halo spectral emissivity test from 3.3 to 50 microns On-orbit T-scale (-40 to +30 C) Phase Change Cell Heated Halo On-orbit Absolute Radiance Standard (OARS) 18 NanoIntegris PureWave Graphene Nanoplatelets Material is composed of thin, highly dispersible graphene nanoplatelets with very low oxygen content. The turbostratic and wavy morphology of the material leads to an unequalled ability to be dispersed in a variety of solvents. 19 Doped Z306 has Ep >0.93 from 2 to 60 m provides a Cavity Emissivity Ec > 0.998 for 40 < Cavity factor < 70 On-Site (LaRC) Measurements of Blackbody Candidate Paints Measured 12/20-21/2010: 8º Total Hemispherical Reflectance Cavity Emissivity (Ec) for different Paint Emissivities (Ep), and different Cavity Factors (Cf). Ec = 1 - (1-Ep) / Cf = 1-Ep Z306 Cavity Facotor Cf (undoped example) 0.07 Ep 40 50 60 70 0.90 0.9975 0.9980 0.9983 0.9986 0.91 0.9978 0.9982 0.9985 0.9987 0.92 0.9980 0.9984 0.9987 0.9989 0.93 0.9983 0.9986 0.9988 0.9990 0.94 0.9985 0.9988 0.9990 0.9991 0.95 0.9988 0.9990 0.9992 0.9993 0.96 0.9990 0.9992 0.9993 0.9994 0.97 0.9993 0.9994 0.9995 0.9996 0.98 0.9995 0.9996 0.9997 0.9997 0.99 0.9998 0.9998 0.9998 0.9999 1.00 1.0000 1.0000 1.0000 1.0000 0.05 Z306 – 2%CNT Z306 – 2% FGS Cavity Carbon Nano Tubes Data from NASA LaRC CLARREO Black Paint Study Lorenzi, Walker, O’ Connell, 2011 Functionalized Graphene Surfaces 20 Required Emissivity to Meet Heated Halo Conservative uncertainty Requirement of 0.0006 Cavity Emissivity (Ec) for different Paint Emissivities (Ep), and different Cavity Factors (Cf). Ec = 1 - (1-Ep) / Cf Cavity Facotor Cf Ec=0.998 Ec=0.999 Ec=1.000 Ep 40 50 60 70 0.90 0.9975 0.9980 0.9983 0.9986 0.91 0.9978 0.9982 0.9985 0.9987 0.92 0.9980 0.9984 0.9987 0.9989 0.93 0.9983 0.9986 0.9988 0.9990 0.94 0.9985 0.9988 0.9990 0.9991 0.95 0.9988 0.9990 0.9992 0.9993 0.96 0.9990 0.9992 0.9993 0.9994 0.97 0.9993 0.9994 0.9995 0.9996 0.98 0.9995 0.9996 0.9997 0.9997 0.99 0.9998 0.9998 0.9998 0.9999 1.00 1.0000 1.0000 1.0000 1.0000 200 A cavity emissivity (Ec) of 0.998 is required to meet the Heated Halo uncertainty requirement of 0.0006. This Ec can be obtained with a paint emissivity (Ep) of 0.93, for Cavity Factors from 40 to 70, as shown in the table at above. 21 Heated Halo Concept and Uncertainty Analysis For a Cavity Emissivity of Ec = 0.998 Requirement is 0.0006 200 If the cavity emissivity (Ec) is 0.998 or better*, from 3.3 µm to 50 µm then the Heated Halo measurement of emissivity will have an uncertainty of better than the required 0.06%. *Can achieve with Ep>0.93 22 Quantum Cascade Laser (QCL) Output: 9.5 µm 80 mW • QCL developed by Harvard under an IIP and brought to TRL 6 through testing under vacuum • ARI will inject the QCL via the Scene Selection Mirror into the OARS and ABB for emissivity comparison, and the Integrating Sphere for ILS measurement •Laser output power is determined by the Instrument Line Shape (ILS) measurement while viewing the Integrating Sphere 23 QCL Interface to ARI FTS Scene Mirror QCL 1st Flat “Periscope Mirror” QCL Injection The QCL is reflected off the center of the Scene Mirror from the back of the optical system, allowing all targets to be illuminated in identical fashion, while being viewed by the FTS. Blackbody 24 OVTS: ABB Emissivity – QCL Compare ABB to OARS emissivity 25 OVTS: OARS Emissivity – QCL Compare ABB to OARS emissivity 26 OVTS: Instrument Line Shape - QCL 27 Integrate QCL Laser into ARI Prototype The Harvard-developed QCL has been temporarily integrated into the ARI Prototype instrument to allow preliminary testing of individual blackbodies and the integrating sphere, without the scene mirror in the path. • Investigate blackbody reflectivity sensitivity with laser injection position and angle. Using the current configuration, Identify optimal position and angle. • Integrate and align the QCL to the ARI Prototype instrument in the “Flight Configuration” that uses the scene mirror to direct the QCL beam into the desired target – OARS, ABB blackbody, or the integrating sphere (this involves drilling a hole through the periscope mirror). • Conduct instrument line shape tests and compare with preliminary testing. • Conduct emissivity tests with both the ABB and OARS 28 Summary and Outline Introduction Instrument Overview Results Conclusion QCL Testing: Bore-sight with HeNe • • Magnetic locking kinematic bases, combination of custom and COTS optomechanical elements Bore-sighted from approximately 10 – 180 cm IR photo From Taylor, et al., 2016 The UW-SSEC ARI: Demonstrated Radiometric Performance (FW3A.3 – OSA FTS 2015) 15-November-2015 29 Summary and Outline Introduction Instrument Overview Results Conclusion OCEM-QCL Testing: Positional Dependence • • Direct injection of laser into blackbody via tip-tilt mirror Measurements to be made at a range of positions across the cone of the blackbody From Taylor, et al., 2016 The UW-SSEC ARI: Demonstrated Radiometric Performance (FW3A.3 – OSA FTS 2015) 15-November-2015 30 Summary and Outline Introduction Instrument Overview Results Conclusion OCEM-QCL Testing: Positional Dependence • • Direct injection of laser into blackbody via tip-tilt mirror Measurements to be made at a range of positions across the cone of the blackbody From Taylor, et al., 2016 The UW-SSEC ARI: Demonstrated Radiometric Performance (FW3A.3 – OSA FTS 2015) 15-November-2015 31 Summary and Outline Introduction Instrument Overview Results Conclusion OSRM-QCL Testing: Direct Injection Configuration HeNe alignment • • QCL Comparison with CO2 laser based ILS results Reference ILS for measurements completed using laser injection via SSM after Taylor, et al., 2016 The UW-SSEC ARI: Demonstrated Radiometric Performance (FW3A.3 – OSA FTS 2015) 15-November-2015 32 Summary and Outline Introduction Instrument Overview Results Conclusion OSRM-QCL Testing: Direct Injection Configuration QCL source IR photo • • Comparison with CO2 laser based ILS results Reference ILS for measurements completed using laser injection via SSM From Taylor, et al., 2016 The UW-SSEC ARI: Demonstrated Radiometric Performance (FW3A.3 – OSA FTS 2015) 15-November-2015 33 Summary and Outline Introduction Instrument Overview Results Conclusion OSRM-QCL and OCEM QCL: Injection via SSM Side View The QCL is reflected off of the center of the Scene Mirror from the back of the optical system, allowing all targets to be illuminated in identical fashion, while being viewed by the FTS. QCL From Taylor, et al., 2016 The UW-SSEC ARI: Demonstrated Radiometric Performance (FW3A.3 – OSA FTS 2015) 15-November-2015 34 2. CLARREO IR Pathfinder on ISS International Space Station 35 US President’s FY2016 Budget Includes a Pathfinder mission to kickoff CLARREO! (Climate Absolute Radiance and Refractivity Observatory) • “The CLARREO Pathfinder mission will demonstrate essential measurement technologies; validate the high accuracy radiometry required for long-term climate studies in support of other Decadal Survey and land imaging missions; and initiate measurements that will benchmark the shortwave reflectance and infrared climate record.” • “NASA plans to host the two CLARREO Pathfinder instruments, Reflected Solar (RS) and Infrared (IR) spectrometers, on the International Space Station in FY 2019.” (budget $77 M) 36 US President’s FY2016 Budget Includes a Pathfinder mission to kickoff CLARREO! (Climate Absolute Radiance and Refractivity Observatory) • “The CLARREO Pathfinder mission will demonstrate essential measurement technologies; validate the high accuracy radiometry required for long-term climate studies in support of other Decadal Survey and land imaging missions; and initiate measurements that will benchmark the shortwave reflectance and infrared climate record.” • “NASA plans to host the two CLARREO Pathfinder instruments, Reflected Solar (RS) and Infrared (IR) spectrometers, on the International Space Station in FY 2019.” (budget $77 M) 37 Message to President Obama- Climate Change: An important opportunity before you step down • Unfortunately, …NASA has decided to proceed with only half of the system called out in (your budget and) the appropriation • I respectfully request that you direct NASA… to devote the relatively small budget… needed to fulfill a commitment to the original intent of the budget item for CLARREO • Proceeding with the infrared spectrometer pathfinder …would likely lead to the early establishment of an essential benchmark on the current climate of the Earth! Sent 11/11/2016 Slide 38 Infrared ISS Pathfinder Mission In addition to highly valuable technical, schedule, and financial risk reduction for the full CLARREO Mission, a long-lived IR Pathfinder offers much more • Early benchmark for starting the clock for establishing global temperature trends to realize the huge financial benefits outlined in Cooke (2015) and Wielicki (2016) • First-ever Far-IR record from space for exploring a major unexplored region of the Earth emitted spectrum • Intercalibration of the international fleet of operational advanced hyper-spectral sounders [CrIS on Suomi NPP (1:30 AM/PM), IASI on Metop (9:30 AM/PM), and future HIRAS on FY3E… (5:30 AM/PM)] Let’s work to find a way soon! Slide 39