TELEDYNE'S HIGH PERFORMANCE INFRARED DETECTORS FOR SPACE MISSIONS - Paul Jerram and James Beletic
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TELEDYNE’S HIGH
PERFORMANCE INFRARED
DETECTORS FOR SPACE
MISSIONS
Paul Jerram and James
Beletic
ICSO October 2018
Teledyne High Performance Image Sensors
Teledyne DALSA Teledyne e2v Space Imaging
Waterloo, Ontario (Design, I&T) Chelmsford, England (Design, Fab, I&T)
Bromont, Quebec (CCD fab) Grenoble, France (Design, I&T)
• Teledyne utilizes leading CMOS foundries for
Teledyne Imaging Sensors Teledyne Judson Technologies fabrication of CMOS image sensors
Camarillo, California Montgomeryville, Pennsylvania • Including staff who work in machine vision
(Design, Fab, I&T) (Design, Fab, I&T) (locations not shown on map), Teledyne employs
100 CMOS image designers and 7 CCD designers
2
Teledyne Image Sensors ‐ Products
• Infrared and visible sensors
• Custom cameras
• Focal plane electronics
• Laser eye protection & sensor protection
Photodiode 1‐D Photodiode Array 320×256 Thermoelectrically
• Infrared detectors, photodiodes & arrays Array cooled packaging
• Detector packaging
• Custom sensors for tactical and space
• Infrared cameras
• Camera electronics
• Integration and test of IR camera systems
Custom Visible & IR Arrays for DoD Space Applications Space Flight Packaging
NASA JWST 4 Mpixel
High Speed (1600 Hz)
Long‐Wave IR camera
for Lab Instrumentation
Compact Camera Electronics
Micro‐CamTM Aircrew Laser Eye Protection
Infrared Microscope 16 Million Pixel
Camera Infrared Astronomy
Array
High Speed Camera for
Tactical Application
3
Tunable Wavelength: Unique property of HgCdTe 4
Hg1-xCdxTe Modify ratio of Mercury and Cadmium to
“tune” the bandgap energy
5.3
HgCdTe crystal is grown by
MBE on CdZnTe Substrates
E g 0.302 1.93 x 0.81 x 0.832 x 5.35 10 T 1 2 x
2 3 4
G. L. Hansen, J. L. Schmidt, T. N. Casselman, J. Appl. Phys. 53(10), 1982, p. 7099
Teledyne’s High Performance IR Sensors for Space Missions
Hybrid CMOS Image Sensor
Readout Circuit
Input signal
• Flux – object and background
Operating Mode
• Integration time
• Frame readout time
• Shutter (rolling, snapshot)
• Multiple storage cells per pixel
• Windows
• Reset (pixel, line, global)
• Event driven
Interface
• Input (analog, digital)
• Output (analog, digital)
• # of readout ports
Detector The functionality Environment
• Wavelength (λ) (“the brains”) of • Temperature
• Quantum Efficiency a CMOS‐based
• Radiation
• Dark current & Noise sensor is
provided by the Other Requirements
• Radiation environment
readout circuit • Linearity
• Persistence
• Anti-blooming
Teledyne’s High Performance IR Sensors for Space Missions
Substrate removed HgCdTe 6
Cosmic Ray Incident Photons
Note that the incident photons must first pass
through the CdZnTe substrate
CdZnTe Substrate
Cosmic rays in the CdZnTe substrate give
fluorescence that creates signal in the HgCdTe
Bulk n-type HgCdTe The substrate will also decrease QE below
1.3µm
p-type HgCdTe p-type HgCdTe
NB schematic is not to scale
indium bump
epoxy
ROIC input
silicon multiplexer
Output
Signal
Substrate removed HgCdTe 7
Note that the incident photons must first pass
through the CdZnTe substrate
AR Coating
Incident Cosmic rays in the CdZnTe substrate give
Photons fluorescence that creates signal in the HgCdTe
Bulk n-type HgCdTe The substrate will also decrease QE below
1.3µm
The substrate is removed down to the HgCdTe
p-type HgCdTe p-type HgCdTe
layer
An AR Coating can now be applied to give
excellent QE down to below 400nm
indium bump
epoxy
ROIC input
silicon multiplexer
Output
Signal
Substrate removed HgCdTe Provides Simultaneous UV‐Vis‐IR
Light Detection
Atmospheric water
vapor absorption bands
at 1400 and 1900 nm
2510 nm
380 nm
JPL AVIRIS‐NG
Imaging Spectrometer
Teledyne’s High Performance IR Sensors for Space Missions
Promise of Fully Depleted HgCdTe
Teledyne’s high quality HgCdTe is getting even better!
Applications will soon benefit from a major reduction in HgCdTe dark current
• For high flux (300K scenes), will double
operating temperature
• Less expensive cooling options
• Longer cooler operating lifetime
• Able to operate LWIR with mini cryo-coolers
• For low flux applications
• Lower dark current at standard oper. Temp.
• Higher operating temperature
• Longer cooler operating lifetime
• Status
• Demonstrated 10X to 100X reduction in dark
current
• LWIR 128x128, 1280x480, and 640x512
arrays have been tested
• MWIR operated up to 250K
• LWIR operated up to 160K
• Strong funding for development
• Developing partnerships with aerospace
primes for system insertion
• Will utilize for commercial instrumentation
products
9
CHROMATM (Configurable Hyperspectral Readout for Multiple Applications)
Optimized for imaging spectrometers (hyperspectral imaging)
CHROMA 1280×480
Programmable, digital input: clocks and biases generated on‐chip Sensor Chip
Analog output, one output every 160 columns (10 MHz pixel rate) Assembly (SCA)
Snapshot, integrate‐while‐read, nearly 100% duty cycle
CTIA unit cell
+ 30 x 30 micron pixel pitch
+ High linearity (>99% linear over full range)
+ Full well sizes (700 ke‐, 1 Me‐, or 5 Me‐) Focal Plane
Formats (columns by rows; spatial by spectral pixels) Electronics (FPE)
+ 640 × 480 Delivered in 2012
+ 1280 × 480 Delivered in 2014
CHROMA used by:
+ 1600 × 480 ROICs fabricated • Several JPL
Focal plane electronics (16 bit, 10 MHz ADCs, CameraLink interface) spectrometers
Windowing available in row direction • CLARREO Pathfinder
Frame readout time scales with number of rows read out on ISS
+ Row readout time is 16.8 microsec
+ Full‐frame rate (480 rows) is 125 Hz
+ Half‐frame rate (240 rows) is 250 Hz
Low power: 90, 150, 180 mW for CHROMA 640, 1280 and 1600 formats
Performance (advertised specs):
Well capacity & Readout Noise Power ROIC
No.
Array Format CDS Noise CDS Noise CDS Noise dissipation at dimensions
Outputs
Well = 0.7M e‐ Well = 1M e‐ Well = 5M e‐ 125 Hz [mW] [mm] Available support equipment:
CHROMA‐320 120 e‐ 145 e‐ 600 e‐ 70 14.4 x 19.4 2 – Focal Plane Electronics (FPE):
CHROMA‐640 120 e‐ 145 e‐ 600 e‐ 90 24.4 x 19.5 4 engineering/lab grade only
CHROMA‐1280 120 e‐ 145 e‐ 600 e‐ 150 43.2 x 19.6 8 – Flex Cables: warm and cold cables,
CHROMA‐1600 120 e‐ 145 e‐ 600 e‐ 180 52.8 x 19.7 10 engineering/lab grade only
Actual noise performance is 15%-20% lower (better) than listed above
Teledyne’s High Performance IR Sensors for Space Missions 1
0GeoSnap‐18 (Stichable to 3k x 3k)
GeoSnap / CHROMA‐D Design
• 18 micron pitch pixel
• CTIA unit cell with 2 gains / full well
• 100 ke- and 1 Me- or 180 ke- and 2.7 Me-
• Stitchable design, up to 3K×3K pixels
• Snapshot, integrate while read
• Fully digital chip, 14 bit ADCs
• Full frame rate: 120 Hz for 2K×2K, 250 Hz for 3K×512
• ROIC formats fabricated: 2K×2K, 2K×512, 3K×512
• Focal plane arrays made and tested with several types of detectors:
• Visible (Silicon), MWIR (5.3 µm HgCdTe), VLWIR (14.5 µm HgCdTe)
GeoSnap GeoSnap
3K×3K 2K×2K
ROIC Focal Plane Module
• ROIC passed radiation tests (no latchup)
CHROMA‐D • GeoSnap 2K×2K space flight package developed
• GeoSnap 2K×2K in production (TRL 6)
3K×512 • Being used for Visible, MWIR, VLWIR
• CHROMA‐D 2K×512 and 3K×512 being developed
CHROMA‐D for Earth Science applications
1K×512
11Detectors and missions
Teledyne Visible and IR detectors for Euclid
• Euclid is the European Space Agency’s next
flagship astronomy mission.
• Target launch date is 2021.
• Euclid has a 1.2‐m diameter large field of
view telescope with visible and infrared
arrays produced by Teledyne:
• 600 million visible pixels
• 36 4K×4K (16 Mpix) CCDs
• 64 million infrared pixels
• 16 H2RG (4 Mpix) SWIR arrays
• 16 SIDECAR ASIC modules
• Largest IR focal plane array when it launches
• 24 flight candidate H2RGs delivered to NASA
• NASA tested and delivered 20 flight grade
H2RG arrays to ESA, all of which greatly
exceed requirements
Quantum Efficiency
of 24 flight candidate H2RGs
Measured by Goddard SFC Detector
Characterization Laboratory
e2v CCD 273‐84
Teledyne Imaging Sensors
H2RG
2K×2K pixels, 18µm pitch 13H2RG IR Detectors for Euclid
Dark Current at 100K Readout Noise
Median = 0.012 e‐/pix/sec Median = 6.8 e‐
More than 5X better 40% better than specification (11.5 e‐)
than specification (0.07 e‐/pix/sec)
2.3 µm cutoff wavelength
14NASA WFIRST Mission
• H4RG‐10: 4K×4K pixels, 10 µm pixel pitch
2.4 meter
telescope
• Technology Maturation (2014‐2018) achieved all goals
• Reduced H4RG‐10 noise
• Increased operability of 16 megapixel IR arrays
• Demonstrated H4RG‐10 flight performance
• Demonstrated yield for flight production
• Made the arrays flatter (smaller peak‐to‐valley)
• Reduced image persistence
• Flight Production commenced in June 2018
Measured by the Detector Characterization Lab, Goddard Space Flight Center
15Missions for Jupiter and it’s neighborhood
JUICE MAJIS Lucy Europa
VIS‐IR Spectrometer L’Ralph Clipper
Vis‐IR MISE
Jupiter + Ganymede, Calisto & Europa spectrometer Vis‐IR
Trojan Asteroids spectrometer
Europa
Europa
Image
Here
• MWIR CHROMA‐A
• 1 H1RG SWIR array
320×480
• 1 H1RG MWIR array
• 1 H2RG MWIR array • Focal Plane
• 2 SIDECAR ASIC Modules
Electronics
16NEOCam Asteroid Survey Mission
Image Sensor Requirements
Wavelength (µm) 6 – 10
Operating temperature range (K) 35 – 40
Integration time (s) 10
Dark current (e‐/s/pixel) 45,000
Pixel operability (%) (with all above properties) >90
• NEOCam will fly two mosaics
• 2K×8K MWIR (5 µm cutoff)
• 2K×8K LWIR (10 µm cutoff)
• MWIR H2RG produced for several years for
ground-based astronomy and JWST
• LWIR now made in 2K×2K format (H2RG)
• Largest high performance LWIR
detectors ever made
• Each mosaic will be 4 H2RGs
• Mission will fly 8 H2RGs and 8 SIDECAR
ASIC modules
• Teledyne has developed a new H2RG
package and qualified to TRL-6
• Active program of continued development
17Avaris‐NG First Measurements in Europe
Switzerland June 2018
AVIRIS-NG
Imaging Calibrated Radiance Spectra
Cube
Instrument Calibration LAEGERN Test Site
380 to 2510 nm
5 nm resolution
Teledyne’s High Performance IR Sensors for Space MissionsHigh Speed MWIR‐LWIR Multi‐Spectral Focal Plane Array
• 256×256 pixels
• 40 micron pixel pitch
• 8 spectral channels (4 to 12 µm)
• Full well optimized per channel
• 4 rows (selected) read out per channel
• 30,000 Hz frame rate
• Developed for HySpIRI TIR
JPL FPA measurements (William Johnson & the PHyTIR team)
• Cutoff wavelength = 12.9 µm • Being deployed in ECOSTRESS,
• Operating temp = 60 K installed on the ISS
• Dark current = 183 e-/pix/sec (spec isECOSTRESS first results
First light results from
ECOSSTRESS. Showing the
temperature variation over
LA at different times of the
day.
The ECOsystem Spaceborne
Thermal Radiometer
Experiment on Space
Station (ECOSTRESS) will
measure the temperature of
plants and use that
information to better
understand how much
water plants need and how
they respond to stress
Image Courtesy NASA/JPL‐CaltechIf you are interested in this
technology please come and
talk to Teledyne‐e2v about how
we can meet your needs
21Questions?
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