Ariel is the M4 mission of the ESA’s Cosmic Vision Program 2015-2025, whose aim is to characterize by lowresolution transit spectroscopy the atmospheres of over one thousand warm and hot exoplanets orbiting nearby stars. It has been selected by ESA in March 2018 and adopted in November 2020 to be flown, then, in 2029. It is the first survey mission dedicated to measuring the chemical composition and thermal structures of the atmospheres of hundreds of transiting exoplanets, in order to enable planetary science far beyond the boundaries of the Solar System. The Payload (P/L) is based on a cold section (PLM – Payload Module) working at cryogenic temperatures and a warm section, located within the Spacecraft (S/C) Service Vehicle Module (SVM) and hosting five warm units operated at ambient temperature (253-313 K). The P/L and its electrical, electronic and data handling architecture has been designed and optimized to perform transit spectroscopy from space during primary and secondary planetary eclipses in order to achieve a large set of unbiased observations to shed light and fully understand the nature of exoplanets atmospheres, retrieving information about planets interior and determining the key factors affecting the formation and evolution of planetary systems.
We describe the design of the cryogenic packaging and testing of the Sensor Chip Electronics (SCE) delivered to the Near-Infrared Spectro-Photometer (NISP) instrument for the ESA Euclid mission. The Euclid mission will observe 15 000 deg2 of extragalactic sky1 from the Sun{Earth Lagrange point L2. The payload of the Euclid spacecraft consists of a telescope with 1.2m SiC primary mirror, passively cooled to ~ 125 K, and two focal plane instruments, the visible instrument (VIS) and NISP. At the heart of the NISP instrument is a 4 x 4 mosaic focal plane of Teledyne H2RG infrared detector arrays held at 100K linked using a cryogenic ex cable (CFC) to the SCE at as low as 130 K. The SCE uses the Teledyne SIDECAR Application Specific Integrated Circuit (ASIC) to provide timing, biases, communications, and data conversion for operation of the HAWAII 2 RG (H2RG) Sensor Chip Assembly (SCA) and interfaces to the NISP warm electronics. The SIDECAR ASIC is mounted onto a Silicon Fanout (SiFO) and Invar table support structure and then wirebonded to a printed wiring board assembly (PWB) with passive components and 91-pin nanoconnectors. The PWB is housed within an enclosure which serves as the mechanical and thermal interface to the NISP Support Structure. The qualification and flight SCE were assembled and subjected to environmental testing at the Jet Propulsion Laboratory and then calibrated and tested with the flight lot SCA and CFC at Goddard Space Flight Centers Detector Characterization Lab. The results of the qualification and reliability tests as well as the measured characteristics of the flight SCE will be summarized.
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