PLAnetary Transits and Oscillations of stars (PLATO) is a medium-class mission selected by ESA in the framework of the Cosmic Vision programme. The PLATO Instrument Control ICU is responsible for the management of the scientific payload, the communication with the SVM, and the lossless compression of scientific data before the download to the satellite Mass memory. The ICU requirements have been finalized for the Preliminary Design Review. The resulting technical specification has been used to design a Model Based Software architecture. The first two versions of the PLATO ICU SW have been released and fully validated on the target platform. This paper provides the details of the solutions adopted to cover all implemented services.
ARIEL (Atmospheric Remote-sensing InfraRed Large-survey) is a medium-class mission of the European Space Agency, part of the Cosmic Vision program, whose launch is foreseen by early 2029. ARIEL aims to study the composition of exoplanet atmospheres, their formation and evolution. The ARIEL’s target will be a sample of about 1000 planets observed with one or more of the following methods: transit, eclipse and phase-curve spectroscopy, at both visible and infrared wavelengths simultaneously. The scientific payload is composed by a reflective telescope having a 1m-class elliptical primary mirror, built in solid Aluminium, and two focal-plane instruments: FGS and AIRS. FGS (Fine Guidance System)1 has the double purpose, as suggested by its name, of performing photometry (0.50-0.55 μm) and low resolution spectrometry over three bands (from 0.8 to 1.95 µm) and, simultaneously, to provide data to the spacecraft AOCS (Attitude and Orbit Control System) with a cadence of 10 Hz and contributing to reach a 0.02 arcsec pointing accuracy for bright targets. AIRS (ARIEL InfraRed Spectrometer) instrument will perform IR spectrometry in two wavelength ranges: between 1.95 and 3.9 μm (with a spectral resolution R < 100) and between 3.9 and 7.8 μm with a spectral resolution R < 30. This paper provides the status of the ICU (Instrument Control Unit), an electronic box whose purpose is to command and supply power to AIRS (as well as acquire science data from its two channels) and to command and control the TCU (Telescope Control Unit).
Ariel [1] 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. The operational orbit of the spacecraft is baselined as a large amplitude halo orbit around the Sun-Earth L2 Lagrangian point, as it offers the possibility of long uninterrupted observations in a fairly stable radiative and thermo-mechanical environment. A direct escape injection with a single passage through the Earth radiation belts and no eclipses is foreseen. The space environment around Earth and L2 presents significant design challenges to all spacecraft, including the effects of interactions with Sun radiation and charged particles owning to the surrounding plasma environment, potentially leading to dielectrics charging and unwanted electrostatic discharge (ESD) phenomena endangering the Payload operations and its data integrity. Here, we present some preliminary simulations and analyses about the Ariel Payload dielectrics and semiconductors charging along the transfer orbit from launch to L2 included.
PLATO (PLAnetary Transits and Oscillations of stars) is the third medium-class mission (M3), selected by the European Space Agency (ESA) in 2014 and adopted in 2017 for the Cosmic Vision 2015-2025 scientific program. The launch is scheduled in 2026 from the French Guiana (Kourou) for a nominal in-orbit lifetime of 4 years plus up to 4 years of possible extension. The main purpose of the mission is the discovery and preliminary characterization of many different types of exoplanets down to rocky terrestrial planets orbiting around bright solar-type stars. The PLATO spacecraft will operate from a halo orbit around L2 (the Sun-Earth 2nd Lagrangian Point), a virtual point in space, 1.5 million km beyond Earth as seen from the Sun and its Payload will consist of 26 small telescopes (24 normal and 2 fast), pointing at the same target stars, that provide images every 25 seconds with the normal camera and every 2.5 seconds for the two fast cameras, operating in a close loop with the AOCS (S/C Attitude and Orbit Control System). Each camera (consisting of a telescope, the Focal Plane Assembly and its Front-End Electronics) will host four CCDs producing 20.3 megapixels images adding up to 81.4 megapixels per normal camera and 2.11 gigapixels for the overall Payload (P/L). This huge amount of data cannot be transmitted to the ground and need to be processed on-board by the P/L Data Processing System (DPS) made up of various processing electronic units. The DPS of the PLATO instrument comprises the Normal and Fast DPUs (Data Processing Units) and a single ICU (Instrument Control Unit), in charge of HW and SW lossless data compression and managing the P/L through a SpaceWire (SpW) network. In this paper we will review the status of the Instrument Control Unit (ICU) after its Critical Design Review (CDR) process, performed by ESA and PMC (PLATO Mission Consortium), the results of the performance test preliminary run on the Engineering Model (EM), waiting for the following Engineering and Qualification Model (EQM) and Proto-Flight Model (PFM), and the status of the early models development (Engineering Models 1 and 2, Mass and Thermal Dummy - MTD) that, along with the Boot SW (BSW) burning in PROM readiness, will enable the EQM manufacturing.
KEYWORDS: Field programmable gate arrays, Electronics, Data processing, Power supplies, Image processing, Infrared imaging, Space telescopes, Exoplanets, Infrared spectroscopy, Photometry
ARIEL is an ESA mission whose scientific goal is to investigate exoplanetary atmospheres. The payload is composed by two instruments: AIRS (ARIEL IR Spectrometer) and FGS (Fine Guidance System). The FGS detection chain is composed by two HgCdTe detectors and by the cold Front End Electronics (SIDECAR), kept at cryogenic temperatures, interfacing with the F-DCU (FGS Detector Control Unit) boards that we will describe thoroughly in this paper. The F-DCU are situated in the warm side of the payload in a box called FCU (FGS Control Unit) and contribute to the FGS VIS/NIR imaging and NIR spectroscopy. The F-DCU performs several tasks: drives the detectors, processes science data and housekeeping telemetries, manages the commands exchange between the FGS/DPU (Data Processing Unit) and the SIDECARs and provides high quality voltages to the detectors. This paper reports the F-DCU status, describing its architecture, the operation and the activities, past and future necessary for its development.
The PLAnetary Transits and Oscillations of stars (PLATO) is a space telescope under ESA development. The (PLATO’s) Instrument Control Unit (ICU) is an electronics box that is responsible for the management (MGT) of the payload (P/L), the communication with the Service Module (SVM), and the compression of scientific data before transmitting them as telemetries TMs to the SVM. The ICU receives data from 2 “fast” (F-DPU) each 2.5s and 24 normal Data Processing Units (N-DPU) each 25s. In order to reduce the huge data volume produced on-board by the 104 CCD (4 CCD per camera), for each target star it will be allocated a window, from which all the pixel values will be gathered, forming a small image called “imagette”. These cropped images are compressed by means of a lossless algorithm running in the ICU FPGA and transmitted as Packet Utilization Standard (PUS) packets to SVM. These streamlined transmissions require qualified compression and decompression techniques to preserve images. In this poster we propose a scripting tool that classifies and collects automatically telemetry PUS packets, hosting scientific data and metadata, to reconstruct compressed imagettes on-ground.
The Square Kilometer Array (SKA) project is an international effort to build the world's largest radio telescope, with eventually over a square kilometer of collecting area. For SKA Phase 1, Australia will host the low-frequency instrument with more than 500 stations, each containing around 250 individual antennas, whilst South Africa will host an array of close to 200 dishes. The scale of the SKA represents a huge leap forward in both engineering and research and development towards building and delivering a unique instrument, with the detailed design and preparation now well under way. As one of the largest scientific endeavors in history, the SKA will brings together close to 100 organizations from 20 countries. Every aspect of the design and development of such a large and complex instrument requires state-of-the-art technology and innovative approach. This poster (or paper) addresses some aspects of the SKA monitor and control system, and in particular describes the development and test results of the CSP Local Monitoring and Control prototype. At the SKA workshop held in April 2015, the SKA monitor and control community has chosen TANGO Control System as a framework, for the implementation of the SKA monitor and control. This decision will have a large impact on Monitor an Control development of SKA. As work is on the way to incorporate TANGO Control System in SKA is in progress, we started to development a prototype for the SKA Central Signal Processor to mitigate the associated risks. In particular we now have developed a uniform class schema proposal for the sub-Element systems of the SKA-CSP.
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