euclid near infrared spectrometer and photometer ... · below. the warm electronics will be located...

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Euclid Near Infrared Spectrometer and Photometer instrument concept and first testresults obtained for different breadboards models at the end of phase C

Maciaszek, Thierry; Ealet, Anne; Jahnke, Knud; Prieto, Eric; Barbier, Rémi ; Mellier, Yannick ; Beaumont,Florent; Bon, William ; Bonefoi, Anne ; Carle, MichaelTotal number of authors:16

Published in:Space Telescopes and Instrumentation 2016: Optical, Infrared, and Millimeter Wave

Link to article, DOI:10.1117/12.2232941

Publication date:2016

Document VersionPublisher's PDF, also known as Version of record

Link back to DTU Orbit

Citation (APA):Maciaszek, T., Ealet, A., Jahnke, K., Prieto, E., Barbier, R., Mellier, Y., Beaumont, F., Bon, W., Bonefoi, A.,Carle, M., Toulouse-Aastrup, C., Andersen, M. I., Sørensen, A. N., Jakobsen, P., Hornstrup, A., & Jessen, N. C.(2016). Euclid Near Infrared Spectrometer and Photometer instrument concept and first test results obtained fordifferent breadboards models at the end of phase C. In H. A. MacEwen, G. G. Fazio, & M. Lystrup (Eds.), SpaceTelescopes and Instrumentation 2016: Optical, Infrared, and Millimeter Wave (Vol. 9904). [99040T] SPIE -International Society for Optical Engineering. https://doi.org/10.1117/12.2232941

https://doi.org/10.1117/12.2232941

https://orbit.dtu.dk/en/publications/a3080de3-334b-44d9-a036-5f63628c576c

https://doi.org/10.1117/12.2232941

Euclid Near Infrared Spectrometer and Photometer instrument concept and first test results obtained for different breadboards models at the end of phase C

Thierry Maciaszek: Ctr. National d'Études Spatiales, and LAM (Laboratoire d'Astrophysique d’Astrophysique de Marseille) UMR 7326 (France) Anne Ealet: Ctr. de Physique des Particules de Marseille (France) Knud Jahnke: Max-Planck-Institut für Astronomie (Germany) Eric Prieto: Aix Marseille Université, CNRS, LAM (Laboratoire d'Astrophysique de Marseille) UMR 7326 (France) Rémi Barbier: Institut de Physique Nucléaire de Lyon (France) Yannick Mellier: Institut d'Astrophysique de Paris (France), and Commissariat à l'Énergie Atomique (France) Florent Beaumont, William Bon, Anne Bonefoi, Michael Carle, Amandine Caillat, Anne Costille, Doriane Dormoy, Franck Ducret, Christophe Fabron, Aurélien Febvre, Benjamin Foulon, Jose Garcia, Jean-Luc Gimenez, Emmanuel Grassi, Philippe Laurent, David Le Mignant, Laurent Martin, Christelle Rossin, Tony Pamplona, Patrice Sanchez, Sebastien Vives: Aix Marseille Université, CNRS, LAM (Laboratoire d'Astrophysique de Marseille) UMR 7326, Marseille, (France) Jean Claude Clémens, William Gillard, Mathieu Niclas, Aurélia Secroun, Benoit Serra: Ctr de Physique des Particules de Marseille (France) Bogna Kubik, Sylvain Ferriol: Institut de Physique Nucléaire de Lyon (France) Jérome Amiaux, Jean Christophe Barrière, Michel Berthe: Commissariat à l'Énergie Atomique (France) Cyrille Rosset: Laboratoire Astroparticule et Cosmologie (France) Juan Francisco Macias-Perez : Laboratoire de Physique Subatomique et Cosmologie (France) Natalia Auricchio, Adriano De Rosa, Enrico Franceschi, Gian Paolo Guizzo, Gianluca Morgante, Francesca Sortino, Massimo Trifoglio, Luca Valenziano: INAF - IASF Bologna (Italy) Laura Patrizii, T. Chiarusi, F. Fornari, F. Giacomini, A. Margiotta, N. Mauri, L. Pasqualini, G. Sirri, M. Spurio, M. Tenti, R. Travaglini: INFN Bologna (Italy) Stefano Dusini, F. Dal Corso, F. Laudisio, C. Sirignano, L.Stanco, S.Ventura, Enrico Borsato: INFN Padova (Italy) Carlotta Bonoli, Favio Bortoletto, Andrea Balestra, Maurizio D'Alessandro, Eduardo MedinaCeli, Ruben Farinelli: INAF - Osservatorio Astronimico di Padova (Italy) Leonardo Corcione, Sebastiano Ligori: INAF - Observatorio Astronomico di Torino (Italy) Frank Grupp, Carolin Wimmer: Max-Planck-Institut für extraterrestrische Physik (Germany) Felix Hormuth, Gregor Seidel, Stefanie Wachter: Max-Planck-Institut für Astronomie (Germany) Cristobal Padilla, Mikel Lamensans: Institut de Física d’Altes Energies (IFAE) (Spain) Ricard Casas, Ivan Lloro: Institut de Ciències de l’Espai, IEEC-CSIC (Spain) Rafael Toledo-Moreo, Jaime Gomez, Carlos Colodro-Conde, David Lizán; Space Science and Engineering Lab (SSEL), Universidad Politécnica de Cartagena (Spain) Jose Javier. Diaz; Instituto de Astrofisica de Canarias (Spain) Per B. Lilje: University of Oslo (Norway) Corinne Toulouse-Aastrup, Michael I. Andersen, Anton N. Sørensen, Peter Jakobsen: Dark Cosmology Centre, Niels Bohr Institute, Copenhagen University (Denmark) Allan Hornstrup, Niels-Christian Jessen: DTU Space, Denmark Cédric Thizy: Université de Liège - ULg CSL (Centre Spatial de Liège) Warren Holmes, Ulf Israelsson, Michael Seiffert, Augustyn Waczynski: NASA (USA) René J. Laureijs, Giuseppe Racca, Jean-Christophe Salvignol, Tobias Boenke, Paolo Strada; European Space Agency/ESTEC On behalf of the Euclid Consortium

ABSTRACT

The Euclid mission objective is to understand why the expansion of the Universe is accelerating through by mapping the geometry of the dark Universe by investigating the distance-redshift relationship and tracing the evolution of cosmic structures. The Euclid project is part of ESA's Cosmic Vision program with its launch planned for 2020 (ref [1]). The NISP (Near Infrared Spectrometer and Photometer) is one of the two Euclid instruments and is operating in the near-IR spectral region (900-2000nm) as a photometer and spectrometer. The instrument is composed of: - a cold (135K) optomechanical subsystem consisting of a Silicon carbide structure, an optical assembly (corrector and camera lens), a filter wheel mechanism, a grism wheel mechanism, a calibration unit and a thermal control system - a detection subsystem based on a mosaic of 16 HAWAII2RG cooled to 95K with their front-end readout electronic cooled to 140K, integrated on a mechanical focal plane structure made with molybdenum and aluminum. The detection subsystem is mounted on the optomechanical subsystem structure - a warm electronic subsystem (280K) composed of a data processing / detector control unit and of an instrument control unit that interfaces with the spacecraft via a 1553 bus for command and control and via Spacewire links for science data This presentation describes the architecture of the instrument at the end of the phase C (Detailed Design Review), the expected performance, the technological key challenges and preliminary test results obtained for different NISP subsystem breadboards and for the NISP Structural and Thermal model (STM). Keywords: Euclid, Spectroscopy, Photometry, Infrared, Instrument, NISP

Space Telescopes and Instrumentation 2016: Optical, Infrared, and Millimeter Wave, edited by Howard A. MacEwen, Giovanni G. Fazio, Makenzie Lystrup, Proc. of SPIE Vol. 9904,

99040T · © 2016 SPIE · CCC code: 0277-786X/16/$18 · doi: 10.1117/12.2232941

Proc. of SPIE Vol. 9904 99040T-1

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1. INTRODUCTION Euclid is a wide-field space mission concept dedicated to the high-precision study of dark energy and dark matter. Euclid will carry out an imaging and spectroscopic wide survey of the entire extra-galactic sky (15000 deg2) along with a deep survey covering at least 40 deg2. To achieve these science objectives, the current Euclid reference design consists of a wide field telescope to be placed in L2 orbit by a Soyuz launch with a 6 years’ mission lifetime. The payload consists of a 1.2m diameter 3-mirror telescope with two channels: a VISible imaging channel (VIS) and a Near Infrared Spectrometer and Photometer channel (NISP). Both instruments observe simultaneously the same Field of View (FoV) on the sky and the system design is optimized for a sky survey in a step-and-stare tiling mode. The NISP Instrument is operating in the 920-2000 nm range at a temperature lower than 140K, except for detectors, which are cooled down to ~95 K or below. The warm electronics will be located in the service module, at room temperature (around 20°C). The NISP instrument has two main observing modes: the photometric mode, for the acquisition of images with broad band filters, and the spectroscopic mode, for the acquisition of slitless dispersed images on the detectors. In the photometer mode the NISP instrument images the telescope light in the wavelength range from 920nm to 2000nm (Y, J, H bands). The spatial sampling is required to be 0.3 arcsec per pixel. The FoV of the instrument is 0.55deg2 having a rectangular shape of 0.763deg × 0.722deg. In the spectrometer mode the light of the observed target is dispersed by means of grisms covering the wavelength range of 950 – 1850 nm. In order to provide a flat resolution over the specified wavelength range, four grisms are mounted in a wheel. These four grisms yield three dispersion directions tilted against each other by 90° in order to reduce confusion from overlapping (due to slitless observing mode). The field and waveband definitions used in the individual configurations for spectroscopy and photometry are:

• Three photometric bands: 1. Y Band: 950 − 1192nm 2. J Band: 1192 − 1544nm 3. H Band: 1544 – 2000nm

• Four Slitless spectroscopic bands: 1. Red 0°; 90° and 180° dispersion: 1250 − 1850nm 2. Blue 0° dispersion: 920 − 1300nm

The spectral resolution shall be higher than 250 for a one arcsec homogenous illumination object size. For such an object, the flux limit in spectroscopy shall be lower than 2x10-16 erg·cm-2·s-1 at 1600 nm wavelength. As with all slitless spectrographs, the real resolution varies with the object size (the smaller the size is, higher the resolution is). The image quality of the instrument in flight shall deliver a 50% radius encircled energy better than 0.3 arcsec and a 80% one better than 0.7 arcsec. There is a variation due to diffraction with wavelength. The NISP budgets are presently the following: The instrument sits in a box of 1.0 × 0.6 × 0.5m The total mass of the instrument is 155kg The maximum power consumption is 178W The instrument will produce 290GBit of data per day European Contributor countries for NISP are: France, Italy, Germany, Spain, Denmark and Norway, ESA for the engineering detectors and USA (NASA) for the flight detectors.

2. NISP GLOBAL DESCRIPTION The NISP instrument consists of three main Assemblies

• The NI-OMA (Opto-Mechanical Assembly), composed of the Mechanical Support Structure (NI-SA) and its thermal control (NI-TC), the Optical elements (NI-OA), the Filter Wheel Assembly (NI-FWA), the Grism Wheel Assembly (NI-GWA), the Calibration Unit (NI-CU). The NI-OMA structure supports the Optical elements, the calibration unit, the Filter and Grism Wheel Units and the detection system. It provides the thermo-mechanical interface towards the Euclid PLM.

• The NI-DS (Detector System Assembly) is composed by the Focal Plane Assembly (NI-FPA; the mechanical part of NI-DS) and by the Sensor Chip System (NI-SCS) compose). The NI-DS comprises the 16 H2RG detectors and associated 16 ASICS (Sidecars), passively cooled at operating temperature (<100K for the detectors; 140K for the ASICS Sidecar). Thermal stabilization of the detector is "naturally" obtained thanks to the very good thermal stability provided by the Euclid PLM at the NISP interfaces

• The Warm Electronics Assembly (NI-WE), composed of the Instrument Data Processing Unit and Control Unit (NI-DPU/DCU), and the Instrument Control Unit (NI-ICU). The NI-ICU is managing the commanding and the control of the instrument. It is interfaced with the satellite via a 1553 bus. The NI-DPU/DCU controls the Sensor Chip System and basic image processing such as co-adding (DCU function) and the science onboard data processing, the compression and transfer of scientific data to the S/C Mass Memory using Spacewire links (DPU function). The NI-DPU/DCU functions are regrouped in a single mechanical box for controlling eight detectors. There are two NI-DPU/DCU boxes.

The NI-DS is screwed on the NI-OMA (SiC panel to SiC panel). The NI-OMA+NI-DS is located in the Euclid spacecraft Payload module in a cold environment (130K). The Warm electronic are located in the Euclid spacecraft Service Module at room temperature. A dedicated harness interconnects the NI-OMA, the NI-DS, the NI-WE and different spacecraft electronics boxes



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from room tempel at any of the 3rque (40mN.m) ccked by the bearion is required. W

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Figure 3-8: Y-bRed lines indi

sample, c Calibration UniThe NISP Calibrdifferent infraredThe design is relaSpectralon PTFEthe optics. Control of the LE(ICU). As the unit opera>1.6um. Previous work hathe required wavLEDs is expectedthat the LEDs aredesign. Current developmlayout of the cali

Figure 3-9: Crossthe NISP calibrat

This assembly ha(18µm pitch or 0data to the NI-DP The NISP Detect

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ment steps includibration unit.

s-cut of the NISPtion unit, as used

as the function to0.3 arcsec on the sPU.

tor System (NI-DC panel called P4 ld Plate (CSS) the P4 Sic panel. Apport structure forSensor Chip Systeronic (SCE).

prototypes togethmaximum requiree only. The focus

s in-flight calibratlowing for small-ith 2x5 LEDs (onambertian scatter

d thus received fl

enic conditions, fi

mmercially availamitted them to a ell into the 2017. The structural m

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inding and qualify

able off-the-shelfuniform and contNevertheless, ini

model of the calibr

genic storage and

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by current and du

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ion of the drive si

major challenge,

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Ds as well as fine-

the NISP calibratinclude LEDs, ha

NI-DS) f 4 × 4 IR sensors ut by the NI-DPU

f molybdenum and on the CSS.

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ation of the imagety. t pointing to a sm

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The operating tem140K. Since the very low thermaltime, to all specif SCA/SCE operatimportant for a mfor the NISP appcommon master clocked by the saData and power sinternal distributireasons. The kind of data directives/housekdigital VDD2P5)tested in order tospecific circuits f In particular, the ground/shieldingthermal stable sebare multiplexersthe DPU/DCU elOAPD laboratory SCE boot, configas a reference sysprototype during

Figure 4-2 – LeftSCE reference. C

mperature of the instrument units l noise level. Thisfications in terms

tion synchronismmosaic made of tiplication (see nextclock and all writame master clocksupply connectionion inside the pay

communication (keeping) and the ) have been alread

o evaluate critical for the LVDS com

power supply repg concept as foresections). The SCAs driven by 4× NIlectronics will bey.

guration and data stem, and from th the first tests ma

t side: DCU breadCenter: The Mark

detectors (SCA) facing the detectos configuration als of noise.

m, at the level of a ghtly coupled dett paragraph) and ptings to the SCE

k and started by a ns to each SCE ayload module and

(8 LVDS lines inrequirements for dy baselined and aspects, such as

mmon-mode stab

presentative breaseen in flight withA/SCE focal planeISP SCE operated

e carried out also

acquisition in thehe NISP data conade to boot and dr

dboard under comkury controller ha

Figure

is lower than100Kors are controlledllows the optimiz

single master clotectors with potenpartly by specificinternal registers common pulse.

are done by an unud the service mod

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bilization on the c

d-board will mouh a representativee simulator (moud at flight foreseeinserting a fully o

e NISP standard mntrol units (DCU) rive a Teledyne A

mparative test agandling 4x 8 m cab

4-1: Focal plan o

K while each indd at a temperaturezation of the syste

ock period (10 Mntial electrical croc HW in the DCU(configurations a

usually long doubdule where warm

or the science datapower supply linss is under study ock losses/duplicacritical SCE clock

unt the same DC-e 8m length hybridnted in the same en temperatures inoperational SCE/

mode (multi-accudemonstration m

ASIC.

ainst a Markury Lble harnesses. Ri

overview

dividual readout ee below 135K, theem thermal load o

MHz, 50 nS allocatosstalk. It is ensu

U electronics. Basand command dir

ble-shielded cablelectronics boxes

a port, LVDS synnes (SCE internal

at Airbus DS. Seation and critical

k line.

DC and continuod cable harness (Pstructure shown in a dedicated crySCA mounted on

umulation) is posmodels under test.

LTE controller. Aght side: SCE ab

lectronic (ASIC fe resulting thermaon the satellite rad

ted maximum difured partly by SCEsically, all the SCrectives) are sync

e harness. The les are accommoda

nchronous serial banalog reference

everal preliminarypower supply dr

ous regulators, gaPhBronze for thein the following f

yo-chamber. Finaln a liquid nitrogen

sible both from bLeft side of Figu

A Teledyne ASIC ort/Synchr direct

for digitization) oal emission up to diator and compli

fferential skew buE firmware speci

CE systems are drichronized by shift

ngth is primarily ated and by therm

bidirectional linese Vref, analogic sy configurations hops on the harnes

lvanic insulation thermal gradientfigure) will be bal end-to-end perfon vessel already o

by a Markury LTEure 4-2 shows the

at room temperatives reacting at E

operates at around2.3µm ensures a

ies, at the same

udget), is fically developediven by a t-registers

dictated by mal decoupling

s for upply VDDA andhave already beenss leading to

system and t and Cu for the ased on 4× SCA ormance tests foroperational at the

E controller, usede first DCU

ture is used as EOL boundaries

d a

d

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r

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• Possiband fo

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where

A large amount oprecise charactercapacity and pers A demonstrationoperational temp

The NISP warm Data Processing The full system iCompact PCI bupair. The two Da

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o CPCI Do CPCI Do CPCI Do Powe

Except the DCUsthe low level pre

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E microcode (EleMarkury Scientif

bility to generate or inter-SCE syncnce the reactivitydaries (1.42 S). Tementation of SCeness test. This hadle time erical UTR simule each frame leve

of detector characristics for noise, dsistence (latency)

model, with fourperature, cold defo

electronic is com

g Unit (NI-DPU)

is shown in the els structure with th

ata Processing Unetector Control UFPGA boards

ral Processor Unital spacecraft mem

sting the followinData Processors bData Routers Data Buffer

er Supply

s all the boards in-processing foresp of frames avera

metry Extraction

en already refurbi4-2) for proper op

ctrical Engineerinfic. Several upgra

end of line and fchronization verif

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E/SKA internal Ias been implemen

lator. This is undeel is constant and

cterization has bedark current, conv) (ref [4] and [5])

r detectors has beormation measure

Fi

5mposed of two Da

:

lectrical drawing he exception of th

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n the DPU are colseen in HW consiaging

ished and tested bperation with long

ng Firmware, EEades are foreseen

frame pulses (EOfication Abort and Synch

o achieve synchroInter Pixel Capacinted and is suppor

er implementationthe level increase

een conducted witversion gain, non .

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igure 4-3: 4 View

5. THE NISata Processing Un

reported in figurehe main power sue both including:provide clock and

on board data pr

Maxwell SCS750

ld redundant. Eacisting of:

by the contractor g cable harnesses

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hronize directives onism of operationitance test (IPC erted by an interna

n and allows to pes with a program

th the engineeringlinearity of the p

d tested. Thermalion tests have bee

ws of the NI-DS d

SP WARM Enit (NI-DPU) and

e ”NISP functionupply system and

d power to the rea

rocessing, compre

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(Markury, US) to and with the SCA

iously delivered be collaboration w

SCE acknowledge

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roduce directly bmmable step

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l Balance / Thermen successfully do

demonstration mo

LECTRONICone Instrument C

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o support the NISA mux/SCE oper

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by the SCE simula

will be conducted E, Inter pixel cap

mal Vacuum, condone.

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e data sending the

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ated Multi Accum

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unit is mounted arnaging one SCE/S

e units will prepro

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Figure 5-2: NI-

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the full duplicatioPU, this is accomerface bus: the co

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h one Maxwell bo

Figure 5-1: DPU

in charge of: e spacecraft via a

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design (left) and

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PU board (right).

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Figure 5-3: NI

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6. ONBOARD DATA PROCESSING (SEE REF [8]): The routine science NISP operations foresee 20 fields of observation per day, each one composed by four dithers where four exposures each are taken, for a total maximum assigned science data telemetry of 290 Gbit/day. A dark exposure is taken during the spacecraft slew. This limited amount of allowed telemetry, together with the huge number of frames typically produced by IR detectors operated in multi-accumulation mode, have as a consequence the need to perform part of the processing pipeline directly on-board and to transfer to ground only the final products for each exposure. Moreover, final data must be also compressed to fit with the assigned telemetry throughput. A number of readout modes have been envisioned for the NISP instrument in the various development stages. Multi-accumulation (MACC) is at the moment the preferred modes for both spectrograph and photometer readout. MACC readout is a peculiar Up the Ramp process (UTR) where detector readouts are grouped in contiguous sets of readouts uniformly placed along the accumulated charge ramp. The data processing can be split into two main stages: stage 1 is implemented in the NI-DCU, directly interfaced to the SCS, where the first static basic pre-processing steps are performed, while stage 2, performed in NI-DPU, is devoted to the processing and compression of the final data frames.

Figure 6-1: Pre-processing HW structure connected to 1× SCS single pair (H2RG SCA + SCE) from a total of 16× located inside the SCS system

The software architecture is dictated by the science requirements and depends on the hardware organization, in terms of DPU power, internal memory, available links with both DCU and SVM. During the previous different phases of the project various processing possibilities were analyzed, in terms of computational complexity, DPU internal memory needs, amount of final data and quality of results. As a result, the foreseen on-board pre-processing pipeline7 will be as depicted in Figure 6-2 where the violet blocks represent the operations performed inside the DPUs. This operational flow is sequentially repeated to cover the 17 exposures (4 spectro + 12 photo + 1 dark) to be performed during each single cycle. At the end of the pipeline described in Figure 6-2 final generated data, with their associated header and metadata to properly re-construct images on ground, are transmitted to the spacecraft Mass Memory Unit, to be down-linked to ground. The most crucial constraint for the on-board processing is given by the need to keep up with the on-going observations, so the previous work was mostly concentrated to verify the algorithm performances, especially in terms of time spent. Current development steps include the integration of the data processing with the overall DPU Application Software structure.

Figure 6-2: On-board data processing pipe-line for the Euclid NIS/NIP instrumental modes. The pipe-line is subdivided in three different sections on

the base of the involved hardware, in the order: SCE analog hardware, FPGA hardware and sequential processing hardware



)%

1%

)%

)%

)%

)%

)%

)%

)%

1000 1200 1400'

WavelE

1600 1800 2(

ength (nm)

Optical performThe following fig80% and at 50%

IR detector QE The detector QE values but also th With some detecresponse and Qurecently produce

Figure 7-2: QE m

The homogeneitymean dark has beFrom these first t

mances gure shows the evshall be lower th

and noise perfor

and the detector hat 95% of pixels

tors already prodantum Efficiencyd and 17xxx dete

measurements onphase d

y of the pixel reseen shown to be vtests on Flight pa

valuation of the Ehan the specified o

Figu

rmances:

noise are a majors meet these requi

duced by Teledyny within the (0.92ectors correspond

n the first flight dedetectors produce

sponse is excellevery low around 0arts, we can expec

7. NIS

Encircled Energy ones. The followi

ure 7-1: EE (Enci

r concern for the irements to ensur

ne Imaging Sensor2 – 2.3) band. Theding to the ESA N

etectors between ed shows an impr

nt. The CDS rea0,005 e–/pix/s at ct a very high qua

SP PERFORM

compared to requing figure shows

ircled Energy) pe

future NISP perfre the efficiency o

rs under NASA ce following FigurNRE phase produc

920nm and 2300ovement in the sp

adout noise show100 K with a sharality NIR Focal P

MANCES

uired values (the that NISP compl

erformance evalua

formance. One imof coverage in the

contract, the first res show results frction of 2.3 um cu

0 nm (left). Flat Fpatial homogenei

s the same perforp distribution an

Plan.

17

maximum radiuslies with its optica

ation

mportant goal is toe full survey.

measurements hafrom 18xxx detectutoff H2RGs.

ield images of flity of the pixel res

rmances demonsnd well inside NIS

7184 18223

18221

s of the Encircledal requirement.

o ensure not only

ave shown excelltors correspondin

ight detectors comsponses.

strated during theSP specifications

17184 NRE

18220

d Energy (EE) at

mean specified

ent flat field ng to flight parts

mpared with NRE

e NRE phase. Th.

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he



L_I

110000

120000

in 100000

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O OM Oil OW Oil OM 0exl value (e-/s)

Readout noi se(ADU)

VD DA differential

100 1000

kHz

10000 100000 1000

Number of pixels

1 le isPION velue lH

Pte) value le.)

DARK and NOIThe tables brequirementsmay be expeincreases wi

SCACDSMacMac

Dark

SCACDSMacMac

Dark

Conducted SuscConducted suscewithout perturbat100 MHz band aIn a non-surprisinFigure below repfloor with 0 injec

ISE during DM below summarizes (due to defecticected, noise (wheth temperature. T

17191 (e-)

cc photo (e-) cc spectro (e-)

k current (e-/s)

17245 (e-)

cc photo (e-) cc spectro (e-)

k current (e-/s)

ceptibility: eptibility of Euclidtion injection on

and pixel referencng way, (given th

presents the readoction. The large in

tests e the properties oce grounding schether in spectromThis is well observ

80 K 90 K 100 K

80 K 90 K 100 K

d SCS in nominabias lines betwee

ce correction is vehe specs asked byout noise (in ADUncrease between

Figure 7-3: D

Figure 7-4:

of both Asics undheme during the tmetry or photome

ved with Asic4.

TIS report 10.77 0.009

TIS report 12.56 0.033

Figure 7

al conditions has ben RO electronicsery efficient to pry Teledyne ) the sU), without refere10MHz and 100

Figure 7-6: Cond

Dark and noise in

: Dark current in

der study. Aparttests) , all other vtry mode) is not

Median 16.87 7.52 6.90 0.0145 0.013 0.018

Median 16.68 7.21 6.78 0.0008 0.0033 0.0077

7-5: Dark and noi

been measured ins and SCE (see [8revent its noise tosensitivity of VDDence pixel correctMHz is difficult

ducted susceptibi

n spectromode

photo mode t from the photomvalues are very gvery sensitive to

Error 0.24 1.00 2.05 0.0046 0.0035 0.0037

Error 0.23 0.96 1.90 0.0059 0.0036 0.0032

se results

n differential and 8]). This sensitivit be injected on scDA and Vref is htion, for a 74dBµVto see when refer

ility measuremen

metry noise, whiood and comply

o temperature var

95% R20.87 n10.01 <10.69 <0.025

<0.023 0.032

95% R20.25 n9.60 <10.03 <0.013

<0.013 0.021

common mode bty appears to be qcience data igher than for othV injection on VDrence pixel correc

t

ch is a bit higherwith the science

riations, while da

Requirement n/a < 9.0 < 13.0

< 0.07

Requirement n/a < 9.0 < 13.0

< 0.07

y CDS noise comquite low excepte

her biases. DDA line. Red liction is “on”

r than the sciencrequirements. A

ark current clearly

mparison with anded in the 5MHz-

ne is the noise

ce As

y

d



8000 10000 12000I

14000 16000 16001

Wavelength in A

SNR for a mag AE

f 100

22000

3=24inY@1063 for Tii

150 200longitude galactic

nt = 97.29 s for SNR>5

250

100 10000 12000 .

6.8

6.6

6.4

6.2

6

5.8

5.6

5.4

5.2

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14000 16000 18000

Wavelength in A

- nN

- m- n

20000 22000

Global performThe performanceupdated evaluatio

A NISP optical mperformance of Nof PSFs for both models on the fin To verify the fullsection). Many p2017, and will alperformance. A fperform measurecharacterization aTo meet the scienpoint source with(<0.33, <0.70) arband passes. Theand reflection intstill substantial liuncomfortable siregain control, it remain unchangeslightly overlap. An SNR evaluatiOne example of mreached with mar

Figure 7-8: SNR4) on mAB =24 o

In spectroscopy, estimate the comThe SNR has bee

ances: es for both channeon of the optical t

Figu

model has been buNISP at 95 % (enchanel to verify f

nal instrument an

l NISP performanprior tests will bellow to test the wafull performance ements needed to and validation ofnce requirementsh a high image qurcsec at the centere blue cutoff of thto VIS and transmight would not yeituation of the Y-bwas decided to s

ed, although to opIn any case the fiion has been dowmap is shown on rgins on average

R map (galactic coobject in 3x3 ape

the sensitivity is mpliance with the

en estimated for t

els have been expthroughput inform

ure 7-7: Best estim

uilt with all opticncircled energy, Pfinal performanced will then valida

nce and models, te done first at subarm electronic ancampaign will beprepare flight ca

f the spectroscopi, the imaging mo

uality defined in tr of the Y, J and H

he Y-bandpass wamission into NISPet be passed into Nbandpass being d

shift this edge by ptimize the filter milter band passes

wn for the missionFigure 7 8This aover the referenc

oordinate) Curreerture.

based on the deterequested limit flthe Hα line and is

plored in more demation of each el

mate of the PCE f

cal elements descrPSFs). It has showes. The ground caate the modeling

tests will be done system level nex

nd the focal plan we done then on thelibration, as for ec wavelength sol

ode of the NISP interms of radii of eH bands respectivas before set to beP. However, the sNISP. Together wdefined by a supersome 30nm to thmanufacturing thwill be finely me

n PDR to verify thanalysis allows vece survey (mean S

ent Best Estimate

ection of the Hα llux of 2×10-16 ers shown on the fo

etail during this yement and is give

for photometry on

ribed above usingwn to be well insampaign on the flfor further calibra

e on ground directxt year. Then, priowith 4 detectors. e flight model an

example PSF meaution of the grismnstrument is requencircled energy (vely. The NISP pe at 920nm, givenswitch between thwith the finite edgrposition of dichr

he red and only stahe flight filters mieasured in the lab he sensitivity of terifying that the SSNR = 5.8).

e of the System in

line in galaxies sprg cm−2 s−1 at > ollowing figure.

ear. The current ren in the followin

n the left and spe

g Zemax and has side specificationslight model will bation on flight.

tly on the flight mor to the final inteThis will give a f

nd will allow to veasurements (both m. uired to have a dep(EE50, EE80) of

photometry channn by a fast transitihese two modes wge width of the Yroic and filter edgart the complete iight show very stebefore flight.

the photometric cSNR requirement

n NISP P Y band

pectra in the rang3.5 for all obj

radiometric budgng figure.

ectroscopy on the

been used to perfs. This optical mobe set to verify an

model starting endegration, an electfirst global verificerify first the instphotometric and

pth of YAB, JABf (<0.30, <0.62) arnel has progressedion of the dichroi

was not as fast as Y-filter in NISP thge, potentially varin-band at aroundeep edges but bec

hannel using the (SNR > 5 on a m

d channel. SNR r

ge of redshift of 0jects over the ent

get has been verifi

right

form an evaluatioodel is used also tnd adjust the prec

d 2017 (see detailtrical model will bcation of the full trument functionaspectroscopic) or

B and HAB = 24 mrcsec, (<0.30, <0d with a slight chaic splitting the ligoriginally hoped

his would have crerying over the fied 965nm. The othcome slightly wid

full sky noise evamAB = 24 point s

reached after 3 e

0.7<z<1.8 and is tire wavelength r

ied with an

on of optical to derive a library

cision of these

ls in next be built mid detector chain

alities but also to r a full

mag (5σ) for a .63) arcsec and ange in filter

ght by wavelengthso that at 920nm

eated the eld-of-view. To her filter edges der, so that they

aluation. ource object) is

exposures (out of

computed to range.

y

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Figure 7-9: SNR mcm−2 s−1 @1720

To verify up to sfor spectroscopy distribution to evFor the mission field stray light NISP and the proField stray light completeness. Aeffects of only zoposteriori on a puconditions of enredshift measurem

Figure 7-10: Totindicated by blue The completenesField stray light, values estimated smooth surfaces pointings of the rthe effects of per

By including thegalaxy density wlight from star an

This example is done to give indichain, the complfrom the Euclid s

map (galactic coor0 nm in 4x4 apertu

science level, andis used (Garilli e

valuate the expectPDR, we have stfrom the telescopoject for telescopare the main so

s the in-field straodiacal light, Outurely statistical b

nvironmental conment and redshift

tal noise in spectre points

ss and purity obtaas well as on thefor the success rinterpolating overeference survey.rsistency, in-Field

e stray light and awith good redshiftnd star density on

only indicative aication that scientlete masking prosurvey. This work

rdinate) Current Beure.

d to take into accet al. 2014) usingted completenesstudied the dependpe, cosmic ray he stray light (ref urces of sensitiv

ay light and persit-of-Field stray liasis. We have simditions, and com

ft validation.

roscopy in functi

ained depend on te redshift and on trate (or completeer the whole surv. Posteriori, we fud stray light and c

after correcting fft for the survey (n the high-level pe

as several improvtific performancecedure, an optimk will be extende

est Estimate of the

count the impact g simulated image and purity of thedence of purity a

hits and persisten[1]) and detector

vity degradation istence effects areight and stellar demulated observati

mputed the compl

ion of star densit

the total noise, dethe line flux. Henness) and purity vey. This alloweurther applied a mcosmic ray hits.

from purity, only (1700 gal/deg²). Berformance of the

vements on the de of Galaxy Clustmized field select

d now at mission

e System in NISP r

of contaminationes from an Euclide resulting selecteand completenessce coming from

r persistence (Serris spectroscopy, te very difficult toensity on the fullions for 12 ‘referleteness and puri

ty for typical poi

efined as the quadnce, for each redsas a function of t

ed us to obtain a mean decrease of

scenarios with tBeyond the NISPe Galaxy Clusteri

data processing antering cannot be aion and field we

n level to optimize

red grism channel.

n of objects in thed NISP simulatored spectroscopic ss on the differentthe H2Rg detectra et al. SPIE 201the other effects

o be taken into acl survey through arence scenarios’ ity through the f

nting in Euclid in

dratic combinationhift and line flux the two variablesvalue for the suc

f 5% in purity and

total noise lower P spectroscopy peing science, as ex

nd the sky modelassessed without eighting scheme, e the survey for b

. SNR after 4 expo

e field, an advancr (Zoubian et al. 2sample. t noise sources: ztors, using the m15) .We have shocontributing for

ccount in the survan E2E simulatio(each covering 1

full chain of ima

n green. The noi

n of noises due tobin, we have fitt

s total noise and ccess rate, compld completeness to

than 1.2 e/s are erformance, we ilxpressed by the to

l are not taken inincluding the fulincluding a seve

both weak lensing

osures on line of flu

ced end-to-end si2014), with a real

zodiacal backgroumost advanced moown that zodiacalr about 5% globavey, we have expon chain, applying

square degree), sge simulation, sp

ise in each simula

o the zodiacal ligted the simulated stellar density, wleteness and purio account (at leas

compliant with thllustrate here the

op level requirem

nto account at thily optimized NIS

ere rejection of dg and clustering s

ux of 2×10-16 erg

imulation pipelinlistic input galaxy

und, in and out oodels provided byl light and Out-ofally on purity anplored in detail thg the other effectspanning differenpectral extraction

ated pointings ar

ht and the Out-ofreference grids o

with correspondinity for each of thst statistically) fo

he requirement o nuisance of strayent.

is stage but it waSP data processindense stellar fieldside.

g

ne y

of y f-d

he ts nt n,

re

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as g

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• To va• To ch

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An EngineeringAn engineering moptics. The NI-DFWA, NI-GWA 100K] for the detThe purpose of ttest at cold opera

At the end of EMOMA and NI-DS The NISP FM mIs expected to be

models to be devetration Model) / Salidate the design heck, at NI-DS levworking together been integrated ann, the measured firn measured in sinthan expected haghly around 13g rces have been meas first quick analnents are as expec

be delivered to E

g Model (EM) / Amodel of NISP w

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M TV test, the DPS electrical simula

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8

eloped are the follSTM (Structural a

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nd successfully terst frequency is vne and random fos been requested for any axis) andeasured. The requlysis show that thcted. The impact

SA as STM in Ju

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or flight. The EMfor the sidecar ele

qualify the functiore and to prepare

PU and the ICU wators will be also

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sceptibility of the ed. ested (see in the Nvery close to the por the structure an

and applied. Thed for random (rouguested interface fhe STM model is of the transient d

uly 2016.

Figure

AVM): d. It will consist oring NI-SCS. Flig

M will be tested unectronics. onal behavior of the full NISP TV

Figure 8-2: NISP

will be delivered t provided.

18.

DELS AND DE

del): re and thermal coNI-SCS (detecto

NI-DS section forprediction (highernd for the differene accelerations onghly between 5 g

forces have been obehavior is as ex

due to the FWA an

e 8-1: NISP STM

of all the NISP sught representativender vacuum at c

NISP (only the nV / performance to

P EM model (pre

to ESA as the Av

EVELOPMEN

ontrol by doing thor/flex cable/sidec

r the NI-DS DM tr by 2Hz) nt subsystem are gn the different pargrms and 10grrm)obtained.

xpected, particularnd GWA activati

M model

ubsystems qualife harness will intecold operational t

nominal side; no o be done on the

liminary concept

vionic Model (AV

NT

he vibration and thcars) and to prove

tests).

generally (not alwrts of the STM ha).

rly, the gradients ion is as expected

fication model (Qerconnect the NI-temperature (135K

redundancy), to pNISP FM.

t)

VM) to be deliver

he TB/TV tests e the auto compat

ways) higher thanave seen quite rea

in the structure ad very low.

QM) excepted theICU, NI-DPU, NK for CU, GWA

perform a conduc

red to ESA in Sep

tibility of four

n expected, then asonable levels

and between the

e structure and thNI-DS, NI-TC, NI

and FWA; [85K

cted susceptibility

ptember 2017. NI

he I-

K-

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I-



ACKNOWLEDGMENTS

We thank ALL the funding agencies of the NISP project: CNES, ASI, DLR, ERDF, MINECO, Norway space agency, Denmark space agency, ESA, NASA and ALL institutes participating to this project.

REFERENCES

[1] G. Racca, et al, "The Euclid mission design", Proc. SPIE 9904-19 (2016) [2] T. Pamplona, et al, "Silicon Carbide main structure for Euclid NISP Instrument in final development", Proc. SPIE 9912, Space Telescopes and Instrumentation 2016: Optical, Infrared, and Millimeter Wave, 9912-21 (2016) [3] A. Costille, et al, "Final design and choices for EUCLID NISP grism", Proc. SPIE 9912, Space Telescopes and Instrumentation 2016: Optical, Infrared, and Millimeter Wave, 9912-82 (2016) [4] B. Kubik, et al, "Low noise flux estimate and data quality control monitoring in EUCLID-NISP cosmological survey", Proc. SPIE TBD (2016) [5] A. Secroun, et al, "Characterization of H2RG IR detectors for the Euclid NISP instrument", Proc. SPIE TBD (2016) [6] J.C Clemens, et al, "EUCLID detector system demonstrator model: a first demonstration of the NISP detection system", Proc. SPIE 9602, UV/Optical/IR Space Telescopes and Instruments: Innovative Technologies and Concepts VII (September 2015) [7] S. Ligori, et al., "Detailed design and first tests of the application software for the instrument control unit of Euclid-NISP", SPIE Conference Series, Vol. 9904, “Space Telescopes and Instrumentation 2016: Optical, Infrared, and Millimeter Wave” (2016) [8] C.Bonoli, et al, "On-board data processing for the Near Infrared Spectrograph and Photometer instrument (NISP) of the EUCLID mission", Proc. SPIE 9912, Space Telescopes and Instrumentation 2016: Optical, Infrared, and Millimeter Wave



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