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The XGIS (X and Gamma Imaging Spectrometer) is one of the three instruments onboard the THESEUS mission (ESA M5, currently in Phase-A). Thanks to its wide field of view and good imaging capabilities, it will efficiently detect and localize gamma-ray bursts and other transients in the 2-150 keV sky, and also provide spectroscopy up to 10 MeV. Its current design has been optimized by means of scientific simulations based on a Monte Carlo model of the instrument coupled to a state-of-the-art description of the populations of long and short GRBs extending to high redshifts. We describe the optimization process that led to the current design of the XGIS, based on two identical units with partially overlapping fields of view, and discuss the expected performance of the instrument., Comment: Proceedings of the SPIE 2020, paper 11444-276

Space Telescopes and Instrumentation 2020: Ultraviolet to Gamma Ray; Virtual, Online; United States; 14 December 2020 through 18 December 2020; Code 166330.--Proceedings of SPIE - The International Society for Optical Engineering Volume 11444, 2020, Article number 114448S.--Full list of authors: Gasent-Blesa, J. L.; Reglero, V.; Connell, P.; Pinazo-Herrero, B.; Navarro-González, J.; Rodríguez-Martínez, P.; Castro-Tirado, A. J.; Caballero-García, M. D.; Amati, L.; Labanti, C.; Mereghetti, S.; Frontera, F.; Campana, R.; Orlandini, M.; Stephen, J.; Terenzi, L.; Evangelisti, F.; Squerzanti, S.; Melchiorri, M.; Fuschino, F. De Rosa, A.; Morgante, G., Within the scientific goals of the THESEUS ESA/M5 candidate mission, a critical item is a fast (within a few s) and accurate (, THESEUS/XGIS instrument is supported by: the ASI-INAF Agreement n. 2018-29-HH.0; the OHB Italia/INAF-OASBo Agreement n.2331/2020/01; the European Space Agency ESA through the M5/NPMC Programme; the AHEAD2020 project funded by the UE through H2020-INFRAIA-2018-2020; the Spanish Ministerio de Ciencia e Innovaci?n, PID2019 109269RB-C41; the Polish National Science Centre, Project 2019/35/B/ST9/03944 and Foundation for Polish Science, Project POIR.04.04.00-00-5C65/17-00. The authors thank all the members of the THESEUS team involved in the development of XGIS instrument.

Space Telescopes and Instrumentation 2020: Ultraviolet to Gamma Ray; Virtual, Online; United States; 14 December 2020 through 18 December 2020; Code 166330.--Proceedings of SPIE - The International Society for Optical Engineering Volume 11444, 2020, Article number 114442K.--Full list of authors: Labanti, C.; Amati, L.; Frontera, F.; Mereghetti, S.; Gasent-Blesa, J. L.; Tenzer, C.; Orleanski, P.; Kuvvetli, I.; Campana, R.; Fuschino, F.; Terenzi, L.; Virgilli, E.; Morgante, G.; Orlandini, M.; Butler, R. C.; Stephen, J. B.; Auricchio, N.; De Rosa, A.; Da Ronco, V.; Evangelisti, F. Melchiorri, M.; Squerzanti, S.; Fiorini, M.; Bertuccio, G.; Mele, F.; Gandola, M.; Malcovati, P.; Grassi, M.; Bellutti, P.; Borghi, G.; Ficorella, F.; Picciotto, A.; Zanini, V.; Zorzi, N.; Demenev, E.; Rashevskaya, I.; Rachevski, A.; Zampa, G.; Vacchi, A.; Zampa, N.; Baldazzi, G.; La Rosa, G.; Sottile, G.; Volpe, A.; Winkler, M.; Reglero, V.; Connell, P. H.; Pinazo-Herrero, B.; Navarro-González, J.; Rodríguez-Martínez, P.; Castro-Tirado, A. J.; Santangelo, A.; Hedderman, P.; Lorenzi, P.; Sarra, P.; Pedersen, S. M.; Tcherniak, D.; Guidorzi, C.; Rosati, P.; Trois, A.; Piazzolla, R., THESEUS (Transient High Energy Sky and Early Universe Surveyor) is one of the three missions selected by ESA as fifth medium class mission (M5) candidates in its Cosmic Vision science program, currently under assessment in a phase A study with a planned launch date in 2032. THESEUS is designed to carry on-board two wide and deep sky monitoring instruments for X/gamma-ray transients detection: a wide-field soft X-ray monitor with imaging capability (Soft X-ray Imager, SXI, 0.3 - 5 keV), a hard X-ray, partially-imaging spectroscopic instrument (X and Gamma Imaging Spectrometer, XGIS, 2 keV - 10 MeV), and an optical/near-IR telescope with both imaging and spectroscopic capability (InfraRed Telescope, IRT, 0.7 - 1.8 µm). The spacecraft will be capable of performing fast repointing of the IRT to the error region provided by the monitors, thus allowing it to detect and localize the transient sources down to a few arcsec accuracy, for immediate identification and redshift determination. The prime goal of the XGIS will be to detect transient sources, with monitoring timescales down to milliseconds, both independently of, or following up, SXI detections, and identify the sources performing localisation at, The Phase A study of the THESEUS/XGIS instrument is supported by ASI-INAF Agreement n. 2018-29-HH.0, OHB Italia/ - INAF-OASBo Agreement n.2331/2020/01, by the European Space Agency ESA through the M5/NPMC Programme and by the AHEAD2020 project funded by UE through H2020-INFRAIA-2018-2020. By the Spanish Ministerio de Ciencia e Innovación, PID2019-109269RB-C41. By Polish National Science Center, Project 2019/35/B/ST9/03944 and Foundation for Polish Science, Project POIR.04.04.00-00-5C65/17-00.

“© 2020 IEEE. Personal use of this material is permitted. Permission from IEEE must be obtained for all other uses, in any current or future media, including reprinting/republishing this material for advertising or promotional purposes, creating new collective works, for resale or redistribution to servers or lists, or reuse of any copyrighted component of this work in other works.”, This paper presents the thermal design of the electronics unit of the instrument Polarimetric Helioseismic Imager, onboard the European Space Agency mission Solar Orbiter. The thermal design procedure, along with the problems encountered during this design phase, and the solutions found to fix them are described, proving in this way the thermal feasibility and robustness of the unit. Its final thermal behaviour, obtained from thermal analyses correlated with data from thermal tests performed in a vacuum environment, is presented. © 1965-2011 IEEE., This work was supported by the Spanish Ministerio de Economia y Conipetitividad under Grant ESP2014-56169-C6-1-R, Grant ESP2014-56169C6-4-R; Grant ESP2014-56169-C6-6-R, Grant ESP2016-77548-05-1-R, Grant ESP2016-77548-05-3-R and Grant ESP2016-77548-05-5-R. The work of.1. Piqueras was supported by the Grant FPU15/0561S "Formacitin do Profesorado Universitario" from the Spanish Ministerio do Educacion; Cultura y Deporte.

Coupling output inductors is a very popular solution when designing a multiple-output DC/DC system. Space-borne circuits are one of the areas where a custom DC/DC converter design with coupled inductors could be preferred to have a detailed design of all variables. Output voltage regulation can be improved using coupled output inductors on a multiple-output DC/DC converter, and, as demonstrated in this paper, it provides an enhanced stability. This paper presents the small signal analysis of a push-pull converter with seven outputs having all its output inductors coupled together and compares it theoretically to the uncoupled version to demonstrate the stability improvement. The theoretical results are validated by simulating a linear model of the circuit and measuring the frequency response on an experimental prototype. Design guidelines and additional benefits of output-coupled inductors are also listed.

This paper calculates the failure rate on reversed polarized silicon diodes with the aim to justify, experimentally, the rules of the European Space Agency (ESA) which are referred to the component life’s extension, the reliability increase and the end of life performance enhancement, by using oversized devices (derating rules). In order to verify the derating rules, 80 silicon diodes are used, which are reverse polarized in a high temperature environment. The diodes are divided in 4 groups of 20 diodes, applying a different voltage to each group, in order to relate the failure rate to the applied derating rule. The experiment described in this paper is developed using a temperature accelerated test to check the leakage current in reverse polarization (HTRB - High Temperature Reverse Bias), with the purpose of obtaining results applying an acceleration factor in order to reduce the test duration. By using a thermal model of the whole system and the equations that describe the reverse polarized diode behaviour, it is possible to stress the 80 diodes up to very high temperature avoiding the runaway effect. Finally, the failure rate is calculated and a revision of the derating rules are proposed by using the experimental result obtained.

EMC requirements for scientific satellites are usually very stringent and much more demanding than terrestrial standards, mainly because ad-hoc scientific instruments developed for the mission require very quiet electromagnetic environments to perform their science. These requirements will assure the compatibility of all instruments on board and with the platform. The electromagnetic noise generated by the DC/DC converter of the PHI instrument, to be flown on board Solar Orbiter, has been drastically reduced applying several different techniques. One technique has been to change the grounding strategy from a single point grounding to a distributed grounding. Two additional techniques were needed to reach the required noise floor. Experimental measurements show the improvements achieved with each technique.

We present a software simulator for the modeling of astronomical instrumentation, which includes platform effects and software processing. It is an end-to-end simulator, from the entrance of the telescope to the data acquisition at the detector, along with software blocks dealing, e.g., with demodulation, inversion, and compression. Developed following the Solar Orbiter/Polarimetric and Helioseismic Imager (SO/PHI) instrument, it comprises elements such as a filtergraph, polarimetric modulator, detector, vibrations, and accumulations. Through these, the simulator performs most of the analyses that can be done with light in astronomy, such as differential photometry, spectroscopy, and polarimetry. The simulator is coded with high flexibility and ease of implementation of new effects and subsystems. Thus, it allows for the user to adapt it to a wide variety of instruments, even not exclusively solar ones, as illustrated with an example of application to a night-time observation. The simulator can provide support in the phase of instrument design and help assess tolerances and test solutions to underperformances arising during the instrument operations. All this makes SOPHISM a very valuable tool for all the stages of astronomical instrument definition, design, operation, and lifetime tracking evaluation. © 2018. The American Astronomical Society. All rights reserved., This work has been partially funded by the Spanish Ministerio de Economia y Competitividad, through Projects ESP2013-47349-C6, ESP2014-56169-C6, and ESP2016-77548-C5, including a percentage from European FEDER funds. It was also supported by Deutsches Zentrum fur Luft-und Raumfahrt (DLR) under project 50 OT 1201. The National Solar Observatory is operated by the Association of Universities for Research in Astronomy (AURA), Inc., under a cooperative agreement with the National Science Foundation.

When using a single DC/DC converter with multiple outputs and having a buck topology, which has one filter inductor per output, the designer can choose to couple these outputs together. This paper demonstrates additional benefits of coupling output inductors together. Apart from saving mass and volume, and due to an improved small signal behaviour it also reduces the output impedance of the regulated output. The paper will analyse a seven output push-pull converter used as a space power converter module and verify the theoretical results with experimental measurements.

Space missions have very stringent mass, volume and also power budgets. This requires very precise knowledge of the power consumption of the whole satellite, not only peak power but also static and long term dynamic power. This calculation becomes very complex if all the operational modes (long term dynamic changes) are taken into account, including the different environmental situations. The power budget of any Power Converter Module (PCM), which includes not only the DC/DC converter but also the distribution unit, depends on the power it delivers and on external factors like temperature and input voltage. We propose to use a linear SPICE model using electronic models of discrete components to reach a high precision model of the power consumption of the PCM. The model has to be complex enough to achieve good precision, but also simple enough to simulate in a short time.

Power converters for experiments that have to fly on board space missions (satellite, launchers, etc.) have very stringent requirements due to its use in a very harsh environment. The selection of a suitable topology is therefore not only based on standard requirements but additional more strict ones have also to be fulfilled. This work shows the design procedure followed to build the Power Converter Module (PCM) for the Polarimetric and Helioseismic Imager (SO/PHI), experiment on board the Solar Orbiter Satellite. The selected topology has been a Push-Pull, for a power level of approximately 35 W and with seven output voltages. Galvanic isolation is needed from primary to secondary, but not between each secondary. Coupled inductors between all outputs have allowed reducing cross regulation. The main design problems solved have been reduction of parasitic capacitance of magnetic elements and peak current control and closed loop design when coupling all output inductors together.

This paper describes the Polarimetric and Helioseismic Imager on the Solar Orbiter mission (SO/PHI), the first magnetograph and helioseismology instrument to observe the Sun from outside the Sun-Earth line. It is the key instrument meant to address the top-level science question: How does the solar dynamo work and drive connections between the Sun and the heliosphere? SO/PHI will also play an important role in answering the other top-level science questions of Solar Orbiter, as well as hosting the potential of a rich return in further science. SO/PHI measures the Zeeman effect and the Doppler shift in the FeI 617.3nm spectral line. To this end, the instrument carries out narrow-band imaging spectro-polarimetry using a tunable LiNbO_3 Fabry-Perot etalon, while the polarisation modulation is done with liquid crystal variable retarders (LCVRs). The line and the nearby continuum are sampled at six wavelength points and the data are recorded by a 2kx2k CMOS detector. To save valuable telemetry, the raw data are reduced on board, including being inverted under the assumption of a Milne-Eddington atmosphere, although simpler reduction methods are also available on board. SO/PHI is composed of two telescopes; one, the Full Disc Telescope (FDT), covers the full solar disc at all phases of the orbit, while the other, the High Resolution Telescope (HRT), can resolve structures as small as 200km on the Sun at closest perihelion. The high heat load generated through proximity to the Sun is greatly reduced by the multilayer-coated entrance windows to the two telescopes that allow less than 4% of the total sunlight to enter the instrument, most of it in a narrow wavelength band around the chosen spectral line., Comment: 36 pages, 41 figures