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