TELEDYNE S HIGH PERFORMANCE INFRARED DETECTORS FOR SPACE MISSIONS Paul Jerram and James Beletic ICSO October 2018
Teledyne High Performance Image Sensors Teledyne DALSA Waterloo, Ontario (Design, I&T) Bromont, Quebec (CCD fab) Teledyne e2v Space Imaging Chelmsford, England (Design, Fab, I&T) Grenoble, France (Design, I&T) Teledyne Imaging Sensors Camarillo, California (Design, Fab, I&T) Teledyne Judson Technologies Montgomeryville, Pennsylvania (Design, Fab, I&T) Teledyne utilizes leading CMOS foundries for fabrication of CMOS image sensors Including staff who work in machine vision (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 Infrared detectors, photodiodes & arrays Detector packaging Custom sensors for tactical and space Infrared cameras Camera electronics Integration and test of IR camera systems Photodiode 1 D Photodiode Array 320 256 Array Thermoelectrically cooled packaging Custom Visible & IR Arrays for DoD Space Applications High Speed (1600 Hz) Long Wave IR camera for Lab Instrumentation Space Flight Packaging NASA JWST 4 Mpixel Compact Camera Electronics Micro Cam TM Infrared Microscope Camera Aircrew Laser Eye Protection 16 Million Pixel Infrared Astronomy Array High Speed Camera for Tactical Application 3
Tunable Wavelength: Unique property of HgCdTe Hg 1-x Cd x Te Modify ratio of Mercury and Cadmium to tune the bandgap energy 4 5.3 HgCdTe crystal is grown by MBE on CdZnTe Substrates 2 E g 0.302 1.93x 0.81x 0.832 x 5.35 10 T 1 2x G. L. Hansen, J. L. Schmidt, T. N. Casselman, J. Appl. Phys. 53(10), 1982, p. 7099 3 4 Teledyne s High Performance IR Sensors for Space Missions
Hybrid CMOS Image Sensor Detector Wavelength (λ) Quantum Efficiency Dark current & Noise Radiation environment Persistence The functionality ( the brains ) of a CMOS based sensor is provided by the readout circuit 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 Environment Temperature Radiation Other Requirements Linearity Anti-blooming Teledyne s High Performance IR Sensors for Space Missions
Substrate removed HgCdTe Cosmic Ray Incident Photons 6 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 epoxy ROIC input indium bump silicon multiplexer Output Signal
Substrate removed HgCdTe 7 AR Coating Incident Photons Note that the incident photons must first pass through the 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 The substrate is removed down to the HgCdTe layer epoxy ROIC input indium bump silicon multiplexer An AR Coating can now be applied to give excellent QE down to below 400nm 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
CHROMA TM (Configurable Hyperspectral Readout for Multiple Applications) Optimized for imaging spectrometers (hyperspectral imaging) Programmable, digital input: clocks and biases generated on chip Analog output, one output every 160 columns (10 MHz pixel rate) 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 ) Formats (columns by rows; spatial by spectral pixels) + 640 480 Delivered in 2012 + 1280 480 Delivered in 2014 + 1600 480 ROICs fabricated Focal plane electronics (16 bit, 10 MHz ADCs, CameraLink interface) Windowing available in row direction Frame readout time scales with number of rows read out + 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): Array Format CDS Noise Well = 0.7M e Well capacity & Readout Noise CDS Noise Well = 1M e CDS Noise Well = 5M e Teledyne s High Performance IR Sensors for Space Missions Power dissipation at 125 Hz [mw] Focal Plane Electronics (FPE) ROIC dimensions [mm] No. Outputs CHROMA 320 120 e 145 e 600 e 70 14.4 x 19.4 2 CHROMA 640 120 e 145 e 600 e 90 24.4 x 19.5 4 CHROMA 1280 120 e 145 e 600 e 150 43.2 x 19.6 8 CHROMA 1600 120 e 145 e 600 e 180 52.8 x 19.7 10 Actual noise performance is 15%-20% lower (better) than listed above CHROMA 1280 480 Sensor Chip Assembly (SCA) CHROMA used by: Several JPL spectrometers CLARREO Pathfinder on ISS Available support equipment: Focal Plane Electronics (FPE): engineering/lab grade only Flex Cables: warm and cold cables, engineering/lab grade only 1 0
GeoSnap 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 3K 3K GeoSnap 2K 2K ROIC Focal Plane Module CHROMA D 3K 512 CHROMA D 1K 512 ROIC passed radiation tests (no latchup) GeoSnap 2K 2K space flight package developed GeoSnap 2K 2K in production (TRL 6) Being used for Visible, MWIR, VLWIR CHROMA D 2K 512 and 3K 512 being developed for Earth Science applications 11
Detectors 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 e2v CCD 273 84 Quantum Efficiency of 24 flight candidate H2RGs Measured by Goddard SFC Detector Characterization Laboratory Teledyne Imaging Sensors H2RG 2K 2K pixels, 18µm pitch 13
H2RG IR Detectors for Euclid Dark Current at 100K Median = 0.012 e /pix/sec More than 5X better than specification (0.07 e /pix/sec) 2.3 µm cutoff wavelength Readout Noise Median = 6.8 e 40% better than specification (11.5 e ) 14
NASA 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 15
Missions for Jupiter and it s neighborhood JUICE MAJIS VIS IR Spectrometer Jupiter + Ganymede, Calisto & Europa Lucy L Ralph Vis IR spectrometer Trojan Asteroids Europa Clipper MISE Vis IR spectrometer Europa Europa Image Here 1 H1RG SWIR array 1 H1RG MWIR array 2 SIDECAR ASIC Modules 1 H2RG MWIR array MWIR CHROMA A 320 480 Focal Plane Electronics 16
NEOCam 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) <200 Read noise (correlated double sample; e ) <30 Quantum efficiency (%) >60 Well depth (e ) >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 17
Avaris NG First Measurements in Europe Switzerland June 2018 AVIRIS-NG Imaging Cube Calibrated Radiance Spectra Instrument Calibration LAEGERN Test Site 380 to 2510 nm 5 nm resolution Teledyne s High Performance IR Sensors for Space Missions
High Speed MWIR LWIR Multi Spectral Focal Plane Array JPL FPA measurements (William Johnson & the PHyTIR team) Cutoff wavelength = 12.9 µm Operating temp = 60 K Dark current = 183 e-/pix/sec (spec is <283 e-/pix/sec) Full well optimized per channel, from 6 to 8 million electrons 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 Being deployed in ECOSTRESS, installed on the ISS Teledyne s High Performance IR Sensors for Space Missions 19
ECOSTRESS 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 Caltech
If you are interested in this technology please come and talk to Teledyne e2v about how we can meet your needs 21
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