ARIEL is ESA’s fourth medium-class mission in the Cosmic Vision program, is scheduled for launch in 2029. The telescope aims to conduct an expansive, unbiased spectroscopic survey, unraveling the complexities of exoplanet atmospheres and interiors to better comprehend the key factors influencing planetary system formation and evolution. The baseline payload features an off-axis Cassegrain telescope (M1-M2), a collimating off-axis parabola (M3), and a plane folding mirror (M4) channeling the collimated beam into two instrument modules. ARIEL’s capabilities span primary and secondary transit spectroscopy (1.10 to 7.80μm), broad-band photometry in the Optical (0.50 − 0.80μm) and Near IR (0.80 − 1.10μm) ranges, and a Fine Guidance System. This work will focus on M1, an aluminum mirror with an unobscured elliptical shape of size 1100 x 730mm. The Surface Error budget for M1 covers low and mid spatial frequencies. The work describes the manufacturing process of the mirror, the method used to quantify surface roughness, the characterization of MSF errors, and the study of the degradation of the system performance due to MSF errors.
PLATO (PLAnetary Transits and Oscillations of stars) is the ESA’s third medium-class mission (M3), adopted in 2017 under the Cosmic Vision 2015-2025 program after selection in 2014. Set for launch in 2026 from French Guiana’s Kourou, its primary goal is to discover and provide an initial bulk characterization of diverse exoplanets, including rocky ones, orbiting bright solar-type stars. Operating from a halo orbit around L2, 1.5 million km from Earth, PLATO’s Payload consists of 26 telescopes (24 normal, 2 fast) capturing images every 25 seconds and 2.5 seconds, respectively. These work in tandem with the AOCS (S/C Attitude and Orbit Control System). Each camera comprises four CCDs, yielding 20.3 MP images—81.4 MP per normal camera and 2.11 gigapixels overall. The onboard P/L Data Processing System (DPS) handles this huge data volume, employing Normal and Fast DPUs along with a single ICU. The ICU manages data compression, overseeing the P/L through a SpaceWire network. This paper provides a comprehensive overview of the Instrument Control Unit’s (ICU) status following the rigorous performance test conducted on the Engineering Model (EM) and its evolution during the development phases of the Engineering Qualification Model (EQM) and Proto-Flight Model (PFM). The content delineates the outcomes derived from the extensive performance test executed on the Engineering Model (EM), detailing the meticulous activities undertaken during the Assembly, Integration, and Verification (AIT/AIV) processes of the EQM. Additionally, it explains the status of the Proto-Flight Model (PFM), offering insights into its development path.
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.
Ariel (Atmospheric Remote Sensing Infrared Exoplanet Large Survey) [1] [2] is the fourth Mission (M4) of the ESA’s Cosmic Vision Program 2015-2025, selected in March 2018 and officially adopted in November 2020 by the Agency, whose aim is to characterize the atmospheres of hundreds of diverse exoplanets orbiting nearby different types of stars and to identify the key factors affecting the formation and evolution of planetary systems. The Mission will have a nominal duration of four years and a possible extension of two years at least. Its launch is presently scheduled for mid 2029 from the French Guiana Space Centre in Kourou on board an Ariane 6.2 launcher in a dual launch configuration with Comet Interceptor. The baseline operational orbit of the Ariel is a large amplitude halo orbit around the second Lagrangian (L2) virtual point located along the line joining the Sun and the Earth-Moon system at about 1.5 million km (~236 RE) from the Earth in the anti-Sun direction. Ariel’s halo orbit is designed to be an eclipse-free orbit as it offers the possibility of long uninterrupted observations in a fairly stable environment (thermal, radiation, etc.). An injection trajectory is foreseen with a single passage through the Van Allen radiation belts (LEO, MEO and GEO near-Earth environments). This is approximated by a worst-case half orbit, prior the injection and transfer to L2, with a duration of 10.5 hours, a perigee of 300 km (LEO), an apogee of 64000 km (GEO and beyond), and an inclination close to 0 degrees. During both the injection trajectory and the final orbit around L2, Ariel will encounter and interact mainly with the Sun radiation and the space plasma environment. In L2 the Ariel spacecraft will spend most of its time in the direct solar wind and the Earth’s magnetosheath with passages through the magnetotail. These three environments, along with LEO and GEO, can lead to the build-up of a net electric charge on the spacecraft and payload conductive and dielectric surfaces leading to the risk of Electro Static Discharges (ESD), potentially endangering the whole Payload integrity and telecommunications to Ground.
The ARIEL mission has the task of conducting a large, unbiased spectroscopic survey of exoplanets, in order to explore the nature of exoplanet atmospheres and interiors and, through this, the key factors affecting the formation and evolution of planetary systems in our galaxy. Ariel is composed of two scientific instrument: one is the FGS which provides the Fine Guidance System capabilities and in addition combines a VIS photometer and a NIR low resolution spectrometer. The other instrument is the Ariel IR Spectrometer (AIRS) which provides spectra with resolution between 30 and 100 on a spectral band between 1.95 and 7.8 micrometers. This paper will focus on the application SW of the Instrument Control Unit of the Ariel mission, which is in charge of controlling the AIRS instrument as well as the Telescope Control Unit (TCU), which controls the M2 Mirror Mechanism (M2M) and provides the temperatures of the Payload. In particular, we will discuss the design of the ASW and the development status of the SW. The Ariel ICU is based on a dual core Leon3-FT processor; the ASW is based on the space profile of the Multiprocessor version of RTEMS 6; we plan to use the multicore nature of the processor to separate the control functions from the data processing part (mainly compression). The ASW implements several standard PUS services, plus a set of instrument specific services for controlling the AIRS Detector Control Units (DCU) and the TCU. We will discuss the results of the coupling tests that have been performed to verify the communications between the ICU and the subsystems (DCUs and TCU), as well as between the ICU and the platform (using a dedicated Spacecraft Interface Simulator)
ARIEL (Atmospheric Remote-sensing InfraRed Large-survey) is the fourth medium-class mission (M4) of the European Space Agency, part of the Cosmic Vision program, whose launch is planned by late 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, in both visible and infrared light. The scientific payload is composed by a reflective telescope having a 1m-class elliptical primary mirror, built in solid Aluminum, and two focal-plane instruments: FGS and AIRS. FGS (Fine Guidance System)3 has the double purpose 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). 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 the AIRS warm front-end (as well as acquire science data from its two channels) and to command and control the TCU (Telescope Control Unit).
The PLATO mission, part of ESA’s Cosmic Vision program, is expected to be launched by 2026 and will focus on discovering exoplanets from gas giants down to small rocky planets. Equipped with telescopes and cameras, including 24 normal and 2 fast cameras, it mainly aims to find Earth-sized planets in the habitable zone of Sun-type stars. The Data Processing System, comprising DPUs and the ICU, manages payload operations, with an On-Board Control Procedures (OBCP) engine enhancing autonomy and flexibility. Written in OCL, OBCPs are independent procedures loaded into the ICU memory, enabling late-stage modifications and regular re-execution, reducing repetitive uploads and conserving bandwidth. In this paper, we present a brief overview of the OCL (On-Board Command) language and its features, as well as the capabilities and benefits of having OBCPs. We also describe the OBCP flight software environment and the OBCP engine implemented in the ASW, along with the features and capabilities of the OBCP for the PLATO mission.
KEYWORDS: Data processing, Technetium, Diagnostics, Control systems, Automation, Data communications, Thulium, Telecommunications, Design, Virtual reality
This paper presents a methodology to automate and accelerate the PLATO Payload (P/L) Boot Software (BSW) testing procedures by presenting a set of pre-programmed TCL scripts with different verification targets, satisfying the BSW requirements. These scripts are conceived in order to run an autonomous regression testing while verifying the BSW core functionalities, and in case of an additional BSW verification is needed, a set of scripts will be available for obtaining an automatic quick health-statement. The present method was proven by carrying out the pre-programmed functional and performance tests on the different PLATO’s BSW versions installed on the ICU development models. The tests performed on these models have proven their effectiveness during the BSW testing process, since the testing time has been greatly reduced and the test results can be archived to maintain a useful record that contemporaneously with the dedicated TCL scripts may assist in future verification of the flight BSW version.
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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