The Athena observatory is the second large class ESA mission to be launched in early 2030's. One of its two instruments on board is the X-ray Integral Field Unit (X-IFU). X-IFU will provide a high energy resolution of 2.5eV at 7keV thanks to cryogenic micro-calorimeter of Transition Edge Sensor (TES). In this paper, we will describe the architecture of the ADR control electronics designed following space constraint rules. In particular, two prototypes have been developed. The first one is a differential low noise amplifier with an equivalent input noise density close to 2nV/√Hz at 1kHz. Together with ruthenium oxide thermometer from Lakeshore are dedicated to 50mK measurement. A goal of a noise below 0.4μK/√(Hz) RMS, twice thermal stability requirement is targeted. The second board uses DC/DC converter followed by a fully integrated low dropout voltage regulator (LDO) to supply the ADR superconducting coil. It will control precisely the voltage applied to the ADR cooler during regulation phase and provide up to 2A current during the recycling phase. Complementary approach regarding ADR regulation using simulation with a simplified model of the ADR in Matlab-Simulink will be presented herein.
The Fast Front End Electronic (F-FEE) is a unit of the payload for the PLATO ESA mission. PLATO aims at finding and characterising a large number of extra solar planetary systems. In order to achieve its scientific objectives, PLATO relies on the analysis of continuous time series of high precision photometric measurements of stellar fluxes. The scientific payload of PLATO is based on a multi-telescope approach, involving a set of 24 ”normal” cameras working at a cadence of 25 s optimized to monitor stars fainter than magnitude 8 (photometry on saturated stars down to magnitude 4 will be possible), plus two ”fast” cameras working at a cadence of 2.5 s, and observing stars in the V range from 4 to 8. Beside providing star brightness measurements for bright stars, the ”fast” cameras also work as fine guidance sensors for the attitude control system of the Spacecraft. Each ”fast” camera is equipped with 4 CCDs with 4510 × 2255 light sensitive pixels each, working in frame transfer mode. In view of the instrument development an Engineering Model (EM) of the F-FEE has been manufactured, assembled and tested. The performance tests have been conducted using artificially generated CCD signals as well as real CCDs, proving the capability of the electronics to satisfy the demanding requirements to fine guidance but also science requirements of the PLATO mission.
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