Euclid near infrared spectrophotometer instrument concept and first test results at the end of phase B

Maciaszek, T; Ealet, A; Jahnke, K.; Prieto, E.; Barbier, R.; Mellier, Y.; Costille, A.; Ducret, F.; Fabron, C.; Gimenez, J.-L.; Grange, R.; Martin, L.; Rossin, C.; Pamplona, T.; Vola, P.; Clemens, J. C.; Smadja, G.; Amiaux, J.; Barriere, J. C.; Berthe, M; De Rosa, A; Franceschi, E.; Morgante, G; Trifoglio, M.; Valenziano, L; Bonoli, C.; Bortoletto, F.; D'Alessandro, M.; Corcione, L.; Ligori, S.; Garilli, B.; Riva, M.; Grupp, F.; Vogel, C.; Hormuth, F.; Seidel, G.; Wachter, S.; Diaz, J. J.; Grañena, F.; Padilla, C.; Toledo, R.; Lilje, Per Barth; Solheim, Bjarte Gees Bokn; Toulouse-Aastrup, C.; Andersen, M.; Holmes, W; Israelsson, U; Seiffert, M.; Weber, C; Waczynski, A.; Laureijs, R. J.; Racca, G.; Salvignol, J.C.; Strada, P.
Journal article; AcceptedVersion; Peer reviewed
View/Open
Year
2014
Permanent link
http://urn.nb.no/URN:NBN:no-46722

CRIStin
1160872

Metadata
Show metadata
Appears in the following Collection
Original version
Proceedings of SPIE, the International Society for Optical Engineering. 2014, 9143, DOI: http://dx.doi.org/10.1117/12.2056702
Abstract
The Euclid mission objective is to understand why the expansion of the Universe is accelerating 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. The NISP (Near Infrared Spectro-Photometer) is one of the two Euclid instruments and is operating in the near-IR spectral region (0.9-2µm) as a photometer and spectrometer. The instrument is composed of: - a cold (135K) optomechanical subsystem consisting of a SiC 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 Teledyne 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 B (Preliminary Design Review), the expected performance, the technological key challenges and preliminary test results obtained on a detection system demonstration model. © (2014) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.

Copyright 2014 Society of Photo Optical Instrumentation Engineers. One print or electronic copy may be made for personal use only. Systematic reproduction and distribution, duplication of any material in this paper for a fee or for commercial purposes, or modification of the content of the paper are prohibited.