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

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2016

Publication Year

2021-02-22T14:14:01Z

Acceptance in OA@INAF

Euclid Near Infrared Spectrometer and Photometer instrument concept and first

test results obtained for different breadboards models at the end of phase C

Title

Maciaszek, Thierry; Ealet, Anne; Jahnke, Knud; Prieto, Eric; Barbier, Rémi; et al.

Authors

10.1117/12.2232941

DOI

http://hdl.handle.net/20.500.12386/30513

Handle

PROCEEDINGS OF SPIE

Series

9904

Number

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PROCEEDINGS OF SPIE

SPIEDigitalLibrary.org/conference-proceedings-of-spie

Euclid Near Infrared Spectrometer

and Photometer instrument concept

and first test results obtained for

different breadboards models at the

end of phase C

Maciaszek, Thierry, Ealet, Anne, Jahnke, Knud, Prieto,

Eric, Barbier, Rémi, et al.

Thierry Maciaszek, Anne Ealet, Knud Jahnke, Eric Prieto, Rémi Barbier, Yannick Mellier, Florent Beaumont, William Bon, Anne Bonnefoi, 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, Sébastien Vives, Jean Claude Clémens, William Gillard, Mathieu Niclas, Aurélia Secroun, Benoit Serra, Bogna Kubik, Sylvain Ferriol, Jérôme Amiaux, Jean Christophe Barrière, Michel Berthe, Cyrille Rosset, Juan Francisco Macias-Perez, Natalia Auricchio, Adriano De Rosa, Enrico Franceschi, Gian Paolo Guizzo, Gianluca Morgante, Francesca Sortino, Massimo Trifoglio, Luca Valenziano, Laura Patrizii, T. Chiarusi, F. Fornari, F. Giacomini, A. Margiotta, N. Mauri, L. Pasqualini, G. Sirri, M. Spurio, M. Tenti, R. Travaglini, Stefano Dusini, F. Dal Corso, F. Laudisio, C. Sirignano, L. Stanco, S. Ventura, E. Borsato, Carlotta Bonoli, Favio Bortoletto, Andrea Balestra, Maurizio D'Alessandro, Eduardo Medinaceli, Ruben Farinelli, Leonardo Corcione, Sebastiano Ligori, Frank Grupp, Carolin Wimmer, Felix Hormuth, Gregor Seidel, Stefanie Wachter, Cristóbal Padilla, Mikel Lamensans, Ricard Casas, Ivan Lloro, Rafael Toledo-Moreo, Jaime Gomez, Carlos Colodro-Conde, David Lizán, Jose Javier Diaz, Per B. Lilje, Corinne Toulouse-Aastrup, Michael I. Andersen, Anton N. Sørensen, Peter Jakobsen, Allan Hornstrup, Niels-Christian Jessen, Cédric Thizy, Warren Holmes, Ulf Israelsson, Michael Seiffert, Augustyn Waczynski, René J. Laureijs, Giuseppe Racca, Jean-Christophe Salvignol, Tobias Boenke, Paolo Strada, "Euclid Near Infrared Spectrometer and Photometer instrument concept and first test results obtained for different breadboards models at the end of phase C," Proc. SPIE 9904, Space Telescopes and Instrumentation 2016: Optical, Infrared, and Millimeter Wave, 99040T (29 July 2016); doi: 10.1117/12.2232941

Event: SPIE Astronomical Telescopes + Instrumentation, 2016, Edinburgh, United Kingdom

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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,

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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 deg}2_{. 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 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

Proc. of SPIE Vol. 9904 99040T-2

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0.W EI

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model results: the

n of the 4 lenses corrector lens is a

Figure 3-3: N range between 1 tional temperatur r one specific tem room temperature

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L1, L2, L3 and c allocated in the C

NISP Optics (phot 132K and 134K. re. For the “cold – mperature of the e) is dependent on

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on.

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A unit with the le

4. The first 3 lens Assembly (CoLA)

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: A Cryo-mechan the optical beam

Figure 3-4: NISP of: A Cryo-mecha

ure in invar. The o

Figure 3-5: NIS

, however at the o e for the used len e. enic operation te s, which provide peratures. cryogenic condit assembly and op erials.

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.

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The Cryomecha

The FWA and th temperatures (12 uncertainty (due are enough to ma which is free is th cryomechanism i

The Grisms (NI

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The Filters

(NI-The three infrare assisted reactive individual layers With a clear aper required coating As the filter are n enough, but furth circularity. This i In previous studi process results in run-up to final fil Both test product transmission >95 After settling for of the transfer fro properties of mor reproducibly mea in agreement wit Ongoing work en and evaluation of anism (NI-CM):

he GWA are moto 20K). It includes a to the bearings fr aintain the wheel he rotation aroun is fully OFF.

I-GS, see ref [3])

mounted on the G have about 14 gro omposed of the g combines four op rism in Suprasil 3 ion, a spectral wa pectral filter done ocus function don of the grisms is g nd Invar. Three bl s. -FI): ed filters (Y, J- an magnetron sputte , resulting in a sta rture of 126mm (t thickness homog not simple flats b hermore the circu is necessary to al ies we have also i n slightly better co

lter production w tions have resulte 5% in the passban r the final filter ba om theoretical de re than 98% in th asured to be <2nm th model predictio ncompasses subst f the coating prop

orized with two id a stepper motor th rictions). When a

position. During nd bearings axis. T

:

GWA, three “red” ooves/mm. grism itself (the op

ptical functions in 3001 made of a gr avefront correctio e by a multilayer ne by the curvatur glued in a mechan lades enable to m

nd H-band) for the ering) process. Ea ack thickness up total diameter 13 geneity and to red ut rather lenses w umference (i.e. sid llow controlled gl investigated the p osmetics of the fi we have produced ed in well reprodu nd worked very w andpass design an esign to real filter he passband. Ther m and well predic ons and within to trate manufacturi perties.

dentical CryoMec hat performs a co arrived at the requ this motion, five The cryomechani Figure 3-6: Cr with a spectral b ptical element) gl n one component: rating engraved o on is done by the c filter deposited o re of the first surf nical Invar M93 ri minimize stresses i

Figur e NISP instrumen ach side of the ~1 to 20um per side 0mm) this requir duce the resulting with ~10m focal l

des of the filter su luing of the filter possibility to use t ilter surfaces, PA IAD prototypes uced transmission well. nd coating metho s. At the time of w rmal shift of the b ctable. Measurem olerance budget.

ing for qualificati

chanisms (CM). T oarse positioning, uired position, the e degrees of freed ism is powered on ryomechanism bre bandpass [1250-1 lued on an invar m :

on the prism hypo curvature of the g on the first surface face of the prism.

ing through 9 flex in the optical elem

re 3-7: Grism ove nt are realized as 12mm thick Supr e.

res the use of coat transmissive wav ength, manufactu ubstrate) has to be

s into their moun the more convent ARMS allows for b

of the H-band filt n properties, i.e. t d we have begun writing, the J-ban bandpass between ments of the subst

ion and flight mod

The CM operates rotating the whe e motor detent tor dom (DOF) are lo nly while actuatio

eadboard model 850 nm] and one mechanical moun otenuse to make t grating grooves, e of the prism, xible blades that ment due to therm

erview

double-sided inte asil 3001 filter su ting machines de vefront error. uring and verifyin

e polished down nts, later to be inte tional ion-assisted better thickness h ter as well as a do the transfer of the n a new series of t nd samples have b n room temperatu

rate bending due dels, test coatings

from room temp el at any of the 3 rque (40mN.m) c cked by the beari on is required. W

“blue” with a sp nt. A baffle is mo the light un-devia

compensate the s mal differences (fr

erference filters c ubstrated is coated

signed for 8-inch ng the uncoated su

to ~2nm RMS ro egrated into the fi d deposition (IAD homogeneity and own-scaled PARM e theoretical desig test coatings on sm been evaluated, s ure and operationa

to internal coatin s of the Y and H

perature down to c 60 positions with ombined with the ings assembly. Th When not operated

ectral bandpass [ ounted on the mou

ated at a chosen w

small CTE differe from 300K to 130

coated with the PA d with a stack of h substrates in ord ubstrates alone is oughness while re ilter wheel assem D) coating approa was chosen for t MS prototype of gn with extended maller substrates showing excellent al temperature (~ ng stresses have b filters and further

cryogenic hin +/-0.3° of e friction torques he only DOF , the 920-1300 nm]. unt. wavelength. In ence between 0K) and to ARMS (plasma up to 200 der to achieve the s complex etaining excellent mble (FWA).

ach. While this that reason. In the

the Y-band filter blocking and for verification t transmission ~130K) has been been found to be r qualification e .

(9)

Baffle

Figure 3-8: Y-b Red lines indi sample, c

Calibration Uni

The NISP Calibr different infrared The design is rela Spectralon PTFE the optics. Control of the LE (ICU). As the unit opera >1.6um. Previous work ha the required wav LEDs is expected that the LEDs are design. Current developm layout of the cali

Figure 3-9: Cross the NISP calibrat

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

1. A SiC 2. A Col on the 3. A sup 4. The S electr

band and H-band cate minimum / m oated on one side

it:

ration Unit allows d wavelengths, all atively simple wi E material. The La ED brightness and ates under cryoge

as shown that com velengths and sub

d to take place we e highly durable. ment steps includ ibration unit.

s-cut of the NISP tion unit, as used

as the function to 0.3 arcsec on the s

PU.

tor System (NI-D C panel called P4 ld Plate (CSS) th e P4 Sic panel. A pport structure for Sensor Chip Syste ronic (SCE).

prototypes togeth maximum require e only. The focus s in-flight calibrat lowing for small-ith 2x5 LEDs (on ambertian scatter d thus received fl enic conditions, fi mmercially availa mitted them to a ell into the 2017. The structural m de long-term cryo

P calibration unit / in the vibration c

4.

acquire the imag sky) and read out DS) is composed b

(to be screwed d at supports the m A baffle (for detec r the Sidecars (SS em (SCS), compo

her with smaller w ements in the pass s term of ~15 frin

tion of the infrare -scale flat field ca ne nominal and re red light is directl lux is performed inding and qualify able off-the-shelf

uniform and cont Nevertheless, ini model of the calibr genic storage and

/ View into one o campaign of the N

THE NISP D

ges by sampling t t by the Sidecar A by:

directly on the SiC mosaic of 4 × 4 de tor protection), a SS). It is fixed on osed of the H2RG witness samples / sband or blocking ges is within 15% ed detector array. alibration and me edundant per wav ly pointed toward by current and du fying suitable LED f devices are not u

trolled assembly itial tests of proo ration unit has pa d lifetime cycle-te

of the custom pro NISP STM. This

DETECTOR

the Field of View ASICs. It is seque

C structure of the etectors. The Cold lso made of moly nto the panel P4 b G sensor with 2.3µ

/ Transmission of g region, respecti % of the theoretic . The unit provide easurements of the elength) inside th ds the detector thr uty cycle regulati Ds has become a usable in our case and packaging pr fing devices, espe assed vibration tes esting of the LED

duced LEDs for t model does not i

SYSTEM (N

w with an array of nced and read ou

NI-OMA). d Plate is made of ybdenum, is fixed by three bipods m µm cut-off (SCA)

f the J band test c ively. / Interferog al prediction deri es stable illumina e detector linearit he calibration uni rough a set of baf ion of the drive si major challenge, e. We have theref rocess. The full fo ecially under cryo sting to confirm t Ds as well as

fine-the NISP calibrat include LEDs, ha

NI-DS)

f 4 × 4 IR sensors ut by the NI-DPU f molybdenum an d on the CSS. made of invar. The

), its cryo-flex ca

oating on BK7 sa gram of a 20mm d ived from Stoney ation of the image

ty.

t pointing to a sm ffles without goin ignal in the instru especially for lo fore procured the formal space qual

ogenic conditions the validity of the -tuning of the inte

tion unit / The str arness and optical

hybridized on m U processing to de nd is held by three e NI-SSS is made able (10 cm) and i ample substrates. diameter J band y's formula. e plane at five mall patch of ng through any of ument control uni nger wavelengths

raw LED dies fo ification of the s, have confirmed e mechanical erior optical ructural model of elements. multiplexers eliver digitalized e titanium bipods e of aluminum.

its ASIC sidecar f t s or d f s

(10)

op

h

I

+

NI-SSS NI-S6 NI-CSS P4 Baffle MB bolt

ME

INIIMMMIN

The operating tem 140K. Since the very low thermal time, to all specif SCA/SCE operat important for a m for the NISP app common master clocked by the sa Data and power s internal distributi reasons. The kind of data directives/housek digital VDD2P5) tested in order to specific circuits f In particular, the ground/shielding thermal stable se bare multiplexers the DPU/DCU el OAPD laboratory SCE boot, config as a reference sys prototype during Figure 4-2 – Left SCE reference. C mperature of the instrument units l noise level. This fications in terms tion synchronism mosaic made of ti plication (see next

clock and all writ ame master clock supply connection ion inside the pay communication ( keeping) and the ) have been alread o evaluate critical

for the LVDS com power supply rep g concept as fores ections). The SCA s driven by 4× NI lectronics will be y.

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

t side: DCU bread Center: The Mark

detectors (SCA) facing the detecto s configuration al s of noise. m, at the level of a

ghtly coupled det t paragraph) and p tings to the SCE k and started by a

ns to each SCE a yload module and (8 LVDS lines in requirements for dy baselined and aspects, such as mmon-mode stab presentative brea seen in flight with A/SCE focal plane ISP SCE operated e carried out also

acquisition in the he NISP data con ade to boot and dr

dboard under com kury controller ha

Figure is lower than100K ors are controlled llows the optimiz single master clo tectors with poten partly by specific internal registers common pulse. are done by an unu

d the service mod n parallel mode fo the most critical the hybrid harne LVDS master clo bilization on the c

d-board will mou h a representative e simulator (mou d at flight foresee inserting a fully o e NISP standard m ntrol units (DCU)

rive a Teledyne A

mparative test aga ndling 4x 8 m cab

4-1: Focal plan o K while each ind d at a temperature zation of the syste ock period (10 M ntial electrical cro c HW in the DCU (configurations a usually long doub dule where warm or the science data

power supply lin ss is under study ock losses/duplica critical SCE clock unt the same DC-e 8m lDC-ength hybrid

nted in the same en temperatures in operational SCE/ mode (multi-accu demonstration m ASIC. ainst a Markury L ble harnesses. Ri overview dividual readout e e below 135K, the em thermal load o MHz, 50 nS allocat osstalk. It is ensu U electronics. Bas and command dir ble-shielded cabl electronics boxes a port, LVDS syn nes (SCE internal at Airbus DS. Se ation and critical k line. DC and continuo d cable harness (P structure shown i n a dedicated cry SCA mounted on umulation) is pos models under test.

LTE controller. A ght side: SCE ab

lectronic (ASIC f e resulting therma on the satellite rad ted maximum dif ured partly by SCE

sically, all the SC rectives) are sync e harness. The le s are accommoda nchronous serial b analog reference everal preliminary power supply dr ous regulators, ga PhBronze for the in the following f yo-chamber. Final n a liquid nitrogen sible both from b Left side of Figu

A Teledyne ASIC ort/Synchr direct

for digitization) o al emission up to diator and compli fferential skew bu E firmware speci CE systems are dri chronized by shift ngth is primarily ated and by therm bidirectional lines e Vref, analogic s

y configurations h ops on the harnes lvanic insulation thermal gradient figure) will be ba l end-to-end perfo n vessel already o by a Markury LTE ure 4-2 shows the

at room tempera tives reacting at E

operates at around 2.3µm ensures a ies, at the same udget), is fically developed iven by a t-registers dictated by mal decoupling s for

upply VDDA and have already been ss leading to

system and t and Cu for the ased on 4× SCA ormance tests for operational at the E controller, used e first DCU ture is used as EOL boundaries d a d d n r d

(11)

The Markury LT also tested (See c temperature. The specific SCE refurbishment at are: • Possib and fo • Enhan bound • Imple • Alive and id • Nume where A large amount o precise character capacity and pers A demonstration operational temp

The NISP warm

Data Processing

The full system i Compact PCI bu pair. The two Da o 8x De using o Centr centra Each DPU is hos o CPCI D o CPCI D o CPCI D o Powe Except the DCUs the low level pre

o Group o Telem

TE system has bee center of Figure 4 E microcode (Ele

Markury Scientif bility to generate or inter-SCE sync nce the reactivity daries (1.42 S). T ementation of SC eness test. This ha

dle time erical UTR simul e each frame leve

of detector charac ristics for noise, d sistence (latency) model, with four perature, cold defo

electronic is com g Unit (NI-DPU) is shown in the el s structure with th ata Processing Un etector Control U FPGA boards ral Processor Unit al spacecraft mem sting the followin

Data Processors b Data Routers Data Buffer er Supply

s all the boards in -processing fores p of frames avera metry Extraction en already refurbi 4-2) for proper op ctrical Engineerin fic. Several upgra end of line and f chronization verif y of the exposure A This is essential to

E/SKA internal I as been implemen lator. This is unde el is constant and

cterization has be dark current, conv ) (ref [4] and [5]) r detectors has be ormation measure Fi

5

mposed of two Da : lectrical drawing he exception of th nits (NI-DPU) are Units (DCU) that p t that finalize the mory

ng boards: based with two M

n the DPU are col seen in HW consi aging

ished and tested b peration with long ng Firmware, EE ades are foreseen frame pulses (EO

fication Abort and Synch o achieve synchro Inter Pixel Capaci nted and is suppor er implementation the level increase

een conducted wit version gain, non

.

een integrated and ement and vibrati

igure 4-3: 4 View

5. THE NIS

ata Processing Un reported in figure he main power su e both including: provide clock and

on board data pr Maxwell SCS750 ld redundant. Eac isting of: by the contractor g cable harnesses EF) has been previ n under interactive L, EOF) on the S hronize directives onism of operation

itance test (IPC e rted by an interna n and allows to p es with a program th the engineering linearity of the p d tested. Thermal ion tests have bee

ws of the NI-DS d

SP WARM E

nit (NI-DPU) and

e ”NISP function upply system and d power to the rea rocessing, compre

ch DCU receives

(Markury, US) to and with the SCA iously delivered b e collaboration w SCE acknowledge to react at end of n and precise exp exposure) by mea al readable registe roduce directly b mmable step g detectors and w pixel response, QE l Balance / Therm en successfully do demonstration mo

LECTRONIC

one Instrument C

nal electrical sche d the 8x DCU boa adout electronic. ess and format the

the data of one 2

o support the NIS A mux/SCE oper by Teledyne and with Markury, the e return line. This f line boundaries posure time stamp ns of simulated e er incremented at by the SCE simula

will be conducted E, Inter pixel cap mal Vacuum, cond

one.

odel

C

Control Unit

(NI-me”, each DPU u ards each one man In addition, these e data sending the

2K × 2K detector

SP specific SCE m rated at ambient a

is now under ver main enhanceme s feature is neede (690 µS) instead p (See right side o exposure on a sele t each EOL, both ated Multi Accum

for the flight dete acitance crosstalk ducted susceptibi

-ICU).

unit is mounted ar naging one SCE/S e units will prepro

em via SpaceWir

from one SIDEC

microcode and and cryogenic rification and ents to the EEF

d for debug tests d of frame

of Figure 4-2 ) ectable pixel grid

during exposure mulation Ramps ectors to obtain k, full-well ility at cold round a shared SCA detection ocess the data re link to the

CAR and perform d

s

(12)

ii

SCS150P

o Extra o Co-ad At this interface one of the Data B configuration is a two available CP The Data Buffer double-buffering A functional dem with a first versio

Instrument Con

• One I

The ICU has two boards, all of the • LVPS transc • CDPU ICU. DAS • DAS rest o ction of sub-sets dded Frame data b

level redundancy Buffer Boards ava

available at each PCI data router bo board allows the g mode to ease the monstrator model on of the applicat

ntrol Unit Hardw

Instrument Contro o sections (nomin em interconnected S (Low Voltage P ceivers for the NI U (Central Data P This module also module. The 155 (Data Acquisition f the NISP instru

of programmed r buffering and Spa y is supported by

ailable in each DP DCU TMTC inte oards.

storage of up to e further data pro of the DPU (with tion SW. ware (NI-ICU): ol Unit (NI-ICU) Interface with th Housekeeping m General power su Command signal (heater constant p nal and redundant

d by means of a b Power Supply): pr I-DPU link (1553 Processing Unit): o includes a RTA 53 transceivers fo n System): this b ument, including t Figure 5-2:

NI-raw detector lines acewire transmis the full duplicatio PU, this is accom erface bus: the co 46+46 averaged ocessing. h one Maxwell bo Figure 5-1: DPU in charge of: e spacecraft via a management upply l to the cryo-mech power is applied t), which are iden backplane motherb

rovides DC/DC c controller logic contains a LEON AX FPGA that ext

r the S/C link and oard features all t the filter and grism

-ICU mechanical

s to be used on gr sion to Data Buff on of DPU hardw mplished by duplic ontrol link based o frames with Tele oard, one DCU b

U (design / Demo

a 1553 bus for the hanism, to the 5 L

in open loop with tical and operate rboard: converters to gene

is actually locate N2-FT CPU embe tends the function d the test connect the analogue acqu m wheels, heater

design (left) and

round for monitor fer Boards ware. Averaged da

cation of the 8x S on the RS485 stan emetry and ancilla oard and one Dat

onstrator model)

e commanding of LED's calibration h power setpoint in cold redundan erate all the neces d in the CPDU bo edded in a MDPA nalities of the MP

tor are also locate uisition and drivi rs, temperature se

EBB of the CDP

ring purposes ata groups can be Spacewire (SpW) ndard can be con ary data from the ta Buffer board) h

f the NISP n source and to th

determined by gr ncy. Each NI-ICU ssary secondary p oard).

A ASIC, which m PDA, with the ma ed in this board. ing electronics th

nsors and calibra

PU board (right).

e configured to be links. The same nfigured to be driv 8x handled detec has been manufac

he NI-OMA and N round operators) U (N or R) is divid

power supplies, a manages all the fun

ain aim of interfac at are used to inte ation LEDs.

e transmitted to redundant ven by one of the ction channels in ctured and tested

NI-DS heaters ded in three as well as the 1553

nctions of the NI cing with the erface with the

3

-Proc. of SPIE Vol. 9904 99040T-10

(13)

I

-The warm electro provides the link power supply for The main challen onboard data pro ground, but as de The ICU Applica instrument comm • TM/T • TC de electr • Globa • Time • NISP • Execu • Contr • Contr • Therm • High • Therm • Mana Instrument Con

The ICU ASW is Telecommand an the specific need A coordinated ef as possible, impl The interface wit which the DPUs defined one, with demanding data p active DPUs.

onic will be place k with the NI-OM

r equipment. nge of the warm e ocessing is compl

escribed later HgC ation SW (ASW) manding. It is in c TC exchange with ecoding and distr ronics, NI-DPU/D al instrument mon management, pro operating mode ution of autonom rol of the calibrati rol of filter wheel mal control (open level handling of mal control of the agement of softwa

ntrol Unit Hardw

s based on RTEM nd Telemetry pac ds of the Euclid pr

ffort is in place w ementation of ser th the DPU is bas are configured as h the aim of reduc processing tasks.

ed in the service m MA and NI-DS. Th

electronics is to p exified by the fac CdTe detectors d

is devoted to ma charge of the follo h S/C CDMU on N ribution to NISP i DCU/SCE nitoring and HK p opagation of OBT management ous functions and ion unit (ON/OFF ls (reference posit n loop) of the NI-F

f macro-command e NI-OMA throug are maintenance,

ware Application

MS real-time oper kets will be based roject.

with the Prime of t rvices between N sed on a second M

s Remote Termin cing as much as p The ICU ASW w

Figure 5-3: NI module of the spa his cable will carr process the amoun ct that the amount eliver lots of fram anage the satellite

owing functions: Nom/Red 1553 li instrument subun packet generation T to the DPUs, T d FDIR algorithm F, intensity level tion, position swi FPA detector col ds submission to gh temperature se memory patch an n Software (ICU rative system, in t d on the Packet U the Spacecraft an NISP and VIS, so MIL-STD-1553 b nals and the ICU a

possible the load will decode the PU

ISP functional ele acecraft at ambien ry LVDS signal f nt of data delivere t of downlink acc me to achieve fina e/platform interfac ink

nits: NI-FWA elec n

M time tagging a ms and processes. and current abso itch)

d-plate through te detector system ensors and heaters

nd dump (EEPRO

U ASW, see ref [7

the space-qualifie Utilization Service d with the VIS C that the SW inter us, similar to the as the Bus Contro of management t US formatted hig

ectrical scheme nt temperature. A for scientific data ed by the detecto cepted to ground al science perform ce, the ICU/DPU

ctronics, NI-GWA

and high level ins

rption handling) emperature senso s OM patching is p 7]): ed version by EDI es (PUS) standard DPU ASW team rfaces with the Sp one used betwee oller. The SW int tasks on the DPU gh level TCs and

A harness under P , housekeeping si r during the integ is very limited. O mances. U interface and all

A electronics,

NI-strument internal

ors and heaters

erformed by the B ISOFT. d, with the imple

in order to ensur pacecraft can be s en the Spacecraft terface and comm processor, since implement the lo

Prime contractor r ignals, control co gration of the foll Only final frames l the functionalitie -CU electronics, synchronizations Boot SW) mentation of serv re a common appr simplified and sta and the Euclid in munication protoc this resource is n ow level sequence responsibility ommand and owing frame. Th can be sent to es related to NI-TC s vices tailored to roach and, as far andardized. nstruments, in

ol is an internally needed for the es towards the tw

e

y o

(14)

SCS Cable Harness MCMR/ LOCK m INKS I RbS -S ¡TO TO/FROMFIRYCUa le SPSCEWA/TIM

pae

eeWR /E ROM RII SCS SYSTEM SCS FROM B M

FEGA FIRM WARE

1% KU FROM B DUAL-PORTED DATA BUFFER CO-ADDED FRpMES BiLM DUT

4-CMD/ M5%/

SOOT DPU SYSTEM

WE SYSTEM: S% DPU PROMA 1% OCU FROM lb CPCI B

S<85

P OCESSEDORTR To MM on SEW pW-MM DUAL PORT DA A RUFFER

CMO /MB/Alarms /Boot

To /F rom ICU on MILLED MAXWELL ZCSTSOSBC 55 Mby@F

Lim

Cane Memory OnCECIRu DMA DPU SYSTEM HMG DETECTOR MACC,,..m MODE IXIS/XIPf Header/Fled Spll

Signal Group Co-Adding

lignai XormaliMtiO

[ol6bits

Check Groups Consistency :

-Co -Added Groups Sequence - Digitai /Analog errors and report

Reference Pixel Filtering and Averaging Upper and tower OM Rows Reference Pixel Filtering and

Averaging Left and Right AM Columns

Saturated Pixel Flagging Reference Correction Weighted, Slope Least -Square Fit

on Ramp DifferenoW

H2RG DETECTOR READOUT MODES

Spectrometer: MACO vaca Photometer i Y.j MACC yeso

h MACC also-Dark: MACCsus FPGA Processing CPU Processing 021-Set aHmmaRVdpn to368g bit (Signal &x') 0e-Intention of Aoereged RNMM<P'vxb Signal !azaleas Compression

xrlossleaCOmpreaion

Report On Results

Final Frame Generation - Telemetry

- Compressed Signal - Compressed o° Science Frame Storage

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

(15)

)% 1% )% )% )% )% )% )% )% 1000 1200 1400 ' WavelE 1600 1800 2( ength (nm) Optical perform

The following fig 80% and at 50%

IR detector QE

The detector QE values but also th With some detec response and Qu recently produce

Figure 7-2: QE m The homogeneity mean dark has be From these first t

mances

gure shows the ev shall be lower th

and noise perfor

and the detector hat 95% of pixels tors already prod antum Efficiency d and 17xxx dete

measurements on phase d y of the pixel res een shown to be v tests on Flight pa

valuation of the E han the specified o

Figu

rmances:

noise are a major s meet these requi duced by Teledyn y within the (0.92 ectors correspond

n the first flight de detectors produce sponse is excelle very low around 0 arts, we can expec

7. NIS

Encircled Energy ones. The followi

ure 7-1: EE (Enci

r concern for the irements to ensur ne Imaging Sensor 2 – 2.3) band. The ding to the ESA N

etectors between ed shows an impr nt. The CDS rea 0,005 e–_{/pix/s at}

ct a very high qua

SP PERFORM

compared to requ ing figure shows

ircled Energy) pe

future NISP perf re the efficiency o

rs under NASA c e following Figur NRE phase produc

920nm and 2300 ovement in the sp adout noise show

100 K with a shar ality NIR Focal P

MANCES

uired values (the that NISP compl

erformance evalua

formance. One im of coverage in the contract, the first res show results fr ction of 2.3 um cu

0 nm (left). Flat F patial homogenei s the same perfo rp distribution an Plan.

17

maximum radius lies with its optica

ation mportant goal is to e full survey. measurements ha from 18xxx detect utoff H2RGs.

ield images of fli ty of the pixel res rmances demons nd well inside NIS

7184 ₁₈₂₂₃

18221

s of the Encircled al requirement.

o ensure not only ave shown excell tors correspondin

ight detectors com sponses. strated during the

SP specifications 17184 NRE 18220 d Energy (EE) at mean specified ent flat field ng to flight parts

mpared with NRE e NRE phase. Th

.

E he

(16)

L_I 110000 120000 in 100000 20000 4.01-0.01 000 00. -8oiaul too um o piN O OM Oil OW Oil OM 0 exl value (e-/s)

Readout noi se(ADU)

VD DA differential 100 1000 kHz 10000 100000 1000 Number of pixels 1 le is PION velue lH

Pte) value le.) DARK and NOI

The tables b requirements may be expe increases wi SCA CDS Mac Mac Dark SCA CDS Mac Mac Dark Conducted Susc Conducted susce without perturbat 100 MHz band a In a non-surprisin Figure below rep floor with 0 injec

ISE during DM

below summarize s (due to defectic ected, noise (whe th 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 Euclid tion injection on and pixel referenc ng way, (given th presents the reado ction. The large in

tests

e the properties o ce grounding sch ether in spectrom This is well observ

80 K 90 K 100 K 80 K 90 K 100 K d SCS in nomina bias lines betwee ce correction is ve he specs asked by out noise (in ADU

ncrease between

Figure 7-3: D

Figure 7-4: of both Asics und heme during the t metry or photome ved with Asic4.

TIS report 10.77 0.009 TIS report 12.56 0.033 Figure 7 al conditions has b en RO electronics ery efficient to pr y Teledyne ) the s U), without refere 10MHz and 100

Figure 7-6: Cond

Dark and noise in

: Dark current in der study. Apart tests) , all other v try 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 in s and SCE (see [8 revent its noise to sensitivity of VDD ence pixel correct

MHz is difficult

ducted susceptibi

n spectromode

photo mode t from the photom values are very g

very 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 sc DA and Vref is h tion, for a 74dBµV

to see when refer

ility measuremen

metry noise, whi ood and comply o temperature var 95% R 20.87 n 10.01 < 10.69 < 0.025 < 0.023 0.032 95% R 20.25 n 9.60 < 10.03 < 0.013 < 0.013 0.021 common mode b ty appears to be q cience data

igher than for oth V injection on VD rence pixel correc

t

ch is a bit higher with 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 com quite low excepte her biases.

DDA line. Red li ction is “on”

r than the scienc requirements. A ark current clearly

mparison with and ed in the 5MHz-ne is the noise ce As y d

(17)

8000 10000 12000 I 14000 16000 16001 Wavelength in A SNR for a mag AE f 100 22000

3=24inY@1063 for Tii

150 200 longitude 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 5 14000 16000 18000 Wavelength in A

- n

N

- m

-

n 20000 22000 Global perform The performance updated evaluatio A NISP optical m performance of N of PSFs for both models on the fin To verify the full section). Many p 2017, and will al performance. A f perform measure characterization a To meet the scien point source with (<0.33, <0.70) ar band passes. The and reflection int still substantial li uncomfortable si regain control, it remain unchange slightly overlap. An SNR evaluati One example of m reached with mar

Figure 7-8: SNR 4) on mAB =24 o In spectroscopy, estimate the com The SNR has bee

ances:

es for both channe on of the optical t

Figu model has been bu NISP at 95 % (en

chanel to verify f nal instrument an l NISP performan prior tests will be llow to test the wa full performance ements needed to and validation of nce requirements h a high image qu rcsec at the center e blue cutoff of th to VIS and transm ight would not ye ituation of the Y-b

was decided to s ed, although to op In any case the fi ion has been dow map is shown on rgins on average

R map (galactic co object in 3x3 ape the sensitivity is mpliance with the en estimated for t

els have been exp throughput inform

ure 7-7: Best estim uilt with all optic ncircled energy, P

final performance d will then valida nce and models, t e done first at sub arm electronic an campaign will be prepare flight ca f the spectroscopi , the imaging mo uality defined in t r of the Y, J and H he Y-bandpass wa mission into NISP et be passed into N

bandpass being d shift this edge by ptimize the filter m

ilter band passes wn for the mission Figure 7 8This a over the referenc

oordinate) Curre erture.

based on the dete requested limit fl the Hα line and is

plored in more de mation of each el

mate of the PCE f cal elements descr PSFs). It has show

es. The ground ca ate the modeling tests will be done system level nex nd the focal plan w

e done then on the libration, as for e c wavelength sol ode of the NISP in

terms of radii of e H bands respectiv as before set to be P. However, the s NISP. Together w defined by a super some 30nm to th manufacturing th will be finely me n PDR to verify th analysis allows ve ce survey (mean S

ent Best Estimate ection of the Hα l lux of 2×10-16 er s shown on the fo

etail during this y ement and is give

for photometry on ribed above using wn to be well ins ampaign on the fl for further calibra e on ground direct xt year. Then, prio

with 4 detectors. e flight model an example PSF mea ution of the grism nstrument is requ encircled energy ( vely. The NISP p e at 920nm, given switch between th with the finite edg rposition of dichr he red and only sta he flight filters mi easured in the lab he sensitivity of t erifying that the S SNR = 5.8).

e of the System in line in galaxies sp rg cm−2 s−1 at > ollowing figure.

ear. The current r en in the followin

n the left and spe g Zemax and has side specifications light model will b ation on flight. tly on the flight m or to the final inte This will give a f nd will allow to ve asurements (both m.

uired to have a dep (EE50, EE80) of photometry chann n by a fast transiti hese two modes w ge width of the Y roic and filter edg art the complete i ight show very ste

before flight. the photometric c SNR requirement

n NISP P Y band pectra in the rang 3.5 V for all obj

radiometric budg ng figure.

ectroscopy on the been used to perf s. This optical mo be set to verify an model starting end egration, an elect first global verific erify first the inst

photometric and pth of YAB, JAB f (<0.30, <0.62) ar nel has progressed ion of the dichroi was not as fast as Y-filter in NISP th ge, potentially var in-band at around eep edges but bec hannel using the

(SNR > 5 on a m

d channel. SNR r ge of redshift of 0 jects over the ent

get has been verifi

right

form an evaluatio odel is used also t nd adjust the prec d 2017 (see detail trical model will b cation of the full trument functiona spectroscopic) or B and HAB = 24 m

rcsec, (<0.30, <0 d with a slight cha

ic splitting the lig originally hoped his would have cre rying over the fie d 965nm. The oth come slightly wid

full sky noise eva mAB = 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 wavelength so 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 h m f

(18)

2000 5000 leo 2 stars/ ?e4 /Deg 5e4 150 200

ong dude gal enic

PZ AI reupuo .PoPPe I!JP!1" 4xa 9 @1600 for Tint = 552.725 s Figure 7-9: SNR m cm−2 s−1 @1720 To verify up to s for spectroscopy distribution to ev For the mission field stray light NISP and the pro Field stray light completeness. A effects of only zo posteriori on a pu conditions of en redshift measurem Figure 7-10: Tot indicated by blue The completenes Field stray light, values estimated smooth surfaces pointings of the r the effects of per By including the galaxy density w light from star an This example is done to give indi chain, the compl from the Euclid s

map (galactic coor 0 nm in 4x4 apertu science level, and is used (Garilli e valuate the expect PDR, we have st from the telescop oject for telescop

are the main so s the in-field stra odiacal light, Out urely statistical b nvironmental con ment and redshift

tal noise in spectr e points ss and purity obta

as well as on the for the success r interpolating ove reference survey. rsistency, in-Field e stray light and a with good redshift

nd star density on only indicative a ication that scient lete masking pro survey. This work

rdinate) Current Be ure.

d to take into acc et al. 2014) using ted completeness tudied the depend pe, cosmic ray h e stray light (ref urces of sensitiv ay light and persi t-of-Field stray li asis. We have sim ditions, and com ft validation.

roscopy in functi ained depend on t e redshift and on t rate (or complete er the whole surv . Posteriori, we fu d stray light and c

after correcting f ft for the survey ( n the high-level pe

as several improv tific performance cedure, an optim k will be extende

est Estimate of the

count the impact g simulated image

and purity of the dence of purity a hits and persisten

[1]) and detector vity degradation i stence effects are ight and stellar de mulated observati mputed the compl

ion of star densit the total noise, de the line flux. Hen ness) and purity vey. This allowe urther applied a m cosmic ray hits. from purity, only (1700 gal/deg²). B erformance of the vements on the d e of Galaxy Clust mized field select d now at mission e System in NISP r of contamination es from an Euclid e resulting selecte and completeness ce coming from r persistence (Serr is spectroscopy, t e very difficult to ensity on the full ions for 12 ‘refer leteness and puri

ty for typical poi efined as the quad nce, for each reds as a function of t ed us to obtain a mean decrease of scenarios with t Beyond the NISP e Galaxy Clusteri data processing an

tering cannot be a ion and field we n level to optimize

red grism channel.

n of objects in the d NISP simulator ed spectroscopic s s on the different the H2Rg detect ra et al. SPIE 201 the other effects o be taken into ac l survey through a rence scenarios’

ity through the f

nting in Euclid in dratic combination hift and line flux the two variables value for the suc f 5% in purity and total noise lower P spectroscopy pe ing science, as ex nd the sky model assessed without eighting scheme, e the survey for b

. SNR after 4 expo

e field, an advanc r (Zoubian et al. 2

sample. t noise sources: z tors, using the m 15) .We have sho contributing for ccount in the surv

an E2E simulatio (each covering 1 full chain of ima

n green. The noi n of noises due to

bin, we have fitt s total noise and ccess rate, compl d completeness to

than 1.2 e/s are erformance, we il xpressed by the to l are not taken in including the ful including a seve both weak lensing

osures on line of flu

ced end-to-end si 2014), with a real zodiacal backgrou most advanced mo own that zodiacal r about 5% globa vey, we have exp on chain, applying

square degree), s ge simulation, sp

ise in each simula o the zodiacal lig ted the simulated stellar density, w leteness and puri o account (at leas compliant with th llustrate here the op level requirem nto account at thi ly optimized NIS ere rejection of d g and clustering s

ux of 2×10-16 erg

imulation pipelin listic input galaxy und, in and out o odels provided by l light and Out-of ally on purity an plored in detail th g the other effect spanning differen pectral extraction

ated pointings ar ht and the Out-of reference grids o with correspondin ity for each of th st statistically) fo he requirement o nuisance of stray ent. is stage but it wa SP data processin dense stellar field

side. g ne y of y f-d he ts nt n, re f-of g he or of y as g ds