The first NASA spacecraft to visit and explore planet Venus since the 1990s will be the Venus Emissivity, Radio science, InSAR, Topography, And Spectroscopy mission (VERITAS) orbiter. The Venus Emissivity Mapper (VEM) onboard the spacecraft is designed for surface mapping of Venus within dedicated atmospheric spectral windows. The instrument will provide global coverage for the detection of thermal emissions like volcanic activity, surface rock composition, water abundance, cloud formation and their dynamics by observing 14 narrow filter bands in the near-infrared to short-wave infrared (NIR, SWIR) range of 790 nm to 1510 nm. An almost identical instrument will be part of ESA’s recently announced EnVision mission to Venus, the VenSpec-M in the Venus Spectroscopy Suite (VenSpec). The utilized photodetector for both missions will be an InGaAs type imaging sensor with integrated thermoelectric (TE) cooling, comprising a 640x512 pixel array with 20 μm pixel pitch.
In general, a space environmental qualification of electronic devices combines its susceptibility to radiation induced single event effects (SEE) and the evaluation of permanent degradation effects due to total ionizing dose (TID) and displacement damage dose (DDD). Following a successful qualification test with heavy-ions focusing on SEE, our imaging sensor was subject to a proton irradiation test campaign at Helmholtz-Zentrum Berlin (HZB) for combined TID and DDD testing. To track the sensor evolution, we subdivided the proton fluence into 10 irradiation steps with intermediate measurements. The collected data provide information on the evolution of dark current, light sensitivity and pixels showing randomtelegraph- noise (RTN) on the sensor during a 5-year mission.
For ESA’s EnVision Mission to Venus, a consortium of three spectrometers from across Europe has been formed to collaborate not only on the management and science aspects, but also on the technical implementation. One important technical goal of the VenSpec suite is to implement a clean, simple and robust interface to the spacecraft and to provide an abstraction layer between the channels and the spacecraft. This is achieved by implementing the Central Control Unit (CCU), which provides a harmonized power and data interface to the spacecraft and allows the channels to design for a simple tailored internal interface to the CCU. The CCU consists of two electrical subsystems, the Data Handling Unit (CCU DHU), developed by the Max Planck Institute for Solar System Research (MPS) in Göttingen and the Institute of Computer and Network Engineering (IDA) in Braunschweig and the Power Supply Unit (CCU PSU), developed by the Instituto de Astrofísica de Andalucía (IAA-CSIC) in Granada, the system responsibility being at the DLR Institute of Planetary Research (DLR-PF) in Berlin. Within this framework, an extended electrical architecture trade-off was performed in 2023 to optimize the system, guaranteeing the requested functionality and complying to requirements from all sides. As a result of the trade-off. a single power and data interface were found to be the most suitable and robust solution considering performance, reliability, Fault Detection Isolation and Recovery (FDIR) and Electromagnetic Compatibility (EMC) considerations as well as the complexity of the associated verification campaign. This paper demonstrates the options that were suggested by the different parties and justifies the final architecture, which has been chosen to achieve the best solution for the VenSpec suite.
We report on the current Venus Emissivity Mapper (VEM) instrument design and development status onboard NASAs Venus Emissivity, Radio science, InSAR, Topography, And Spectroscopy (VERITAS) and ESAs EnVision orbiters. The VEM instrument is a push broom multispectral imager that comprises an optical system based on a sophisticated filter assembly with 14 spectral bands and an InGaAs detector with integrated thermoelectric cooler. A turn window mechanism and a two-staged baffle in front of the optics protect the instrument against contamination and straylight. The instruments nominal mass is approximately 6 kg. VEM opens the path for mapping Venus surface emission with a global coverage of >70%.
PLATO (PLAnetary Transits and Oscillations of stars)1 is the M3 class ESA mission dedicated to the discovery
and study of extrasolar planetary systems by means of planetary transits detection. PLATO Payload Camera
units are integrated and vibrated at CSL before being TVAC tested for thermal acceptance and performance
verification at 3 different test facilities (SRON, IAS and INTA). 15 of the 26 Flight Cameras were integrated,
tested and delivered to ESA for integration by the Prime between June 2023 and June 2024, with the remaining
flight units to be tested by the end of 2024. In this paper, we provide an overview of our serial testing approach,
some of the associated challenges, key performance results and an up-to-date status on the remaining planned
activities.
KEYWORDS: Cameras, Space operations, Stars, Design, Data processing, Control systems, Planets, Scanning tunneling microscopy, Satellites, X band, Exoplanets, Astronomical telescopes, Space telescopes
PLATO (PLAnetary Transits and Oscillations) mission is a space-based optical multi-camera photometer mission of the European Space Agency (ESA) to identify and characterize exoplanets and their hosting stars using two main techniques: planetary transit and asteroseismology. Selected as the M3 (third Medium class mission) of the ESA 2015-2025 Cosmic Vision program, PLATO is scheduled to launch end of 2026 and designed for 4 years of nominal observation. The PLATO spacecraft is composed of a Service Module and a Payload Module. The Service Module comprises all the conventional spacecraft subsystems and the sun shield with attached solar arrays. The Payload Module consists of a highly stable optical bench, equipped with 26 optical cameras covering a global field of view of > 2232deg2. The PLATO spacecraft data is complemented by ground-based observations and processed by a dedicated Science Ground Segment. We describe the mission and spacecraft architecture and provide a view of the current status of development.
A STOP (Structural, Thermal, Optical and Performance) analysis has been conducted on the camera units of the PLATO space mission. The analysis is devoted to the prediction of in-orbit performance metrics that could not be otherwise verified through direct testing. The analysis presented in this paper is restricted to the so-called “static cases” which provide a snapshot of a specified thermal condition. These are intended to evaluate the camera performance over the expected operational temperature range and at zero gravity. We hereby provide a description of the model, the requirements to be tested, the simulation strategy and the performance results.
The Venus Emissivity Mapper (VEM) and the VenSpec-M on the NASA VERITAS and ESA EnVision missions, respectively, are multi-spectral imaging systems designed specifically for mapping the surface of Venus using near-infrared atmospheric windows around 1 μm. VEM/VenSpec- M will provide the first global map of rock types on the surface of Venus as well as constant monitoring for volcanic activity at global (VERITAS) and regional/local (EnVision) scales. The VEM/VenSpec- M verification plan ensures accurate performance and science return of the instrument and includes on-ground and in-flight instrument calibrations as well as supporting laboratory measurements for calibration and scientific data analysis. Pre-flight calibrations encompass geometric, spectral, and radiometric calibrations based on the MERTIS (on BepiColombo) calibration campaign and pipeline. Laboratory work involves the creation of spectral libraries of increasing complexity by measuring the emissivity of Venus analogs under Venus surface conditions. These data will distinguish between basalt and felsic rock types on the Venus surface and may enable the identification of intermediate compositions based on iron content. Data analysis uses machine learning models for classification between basalt and felsic rocks and regression to predict FeO content using laboratory calibration data. The data verification plan outlined here not only provides fundamental data needed for VEM/VenSpec-M, but can also be adapted to create data products suitable for calibration of the VenDi (Venus Descent Imager) instrument on the DAVINCI mission. Such use of an integrated calibration plan will benefit all three missions and produce coordinated results that can be directly compared.
In June 2020 NASA has selected the VERTIAS Discovery mission to Venus for flight. The Venus Emissivity Mapper (VEM) provided by DLR together with the VISAR radar system provided by JPL are the core payload of the mission. VEM is the first flight instrument designed with a focus on mapping the surface of Venus using atmospheric windows around 1 μm wavelength. It will provide a global map of surface composition by observing with six narrow band filters from 0.86 to 1.18 μm. Continuous observation of Venus’ thermal emission will place tight constraints on current day volcanic activity. Eight additional channels provide measurements of atmospheric water vapor abundance as well as cloud microphysics and dynamics and permit accurate correction of atmospheric interference on the surface data. Combining VEM with a high-resolution radar mapper on the NASA VERITAS and ESA EnVision missions will provide key insights in the divergent evolution of Venus. After several years of pre-development including the setup of a laboratory prototype the implementation for flight has started with the qualification of the flight detectors, the review of all requirements flowdowns as well as the finalizing of spacecraft interfaces.
KEYWORDS: Radiometry, Sensors, Information operations, Calibration, Bolometers, Thermography, Microbolometers, Signal to noise ratio, Radio optics, Optical filters
TMAP is a high spatial resolution thermal imager, optimized for observing Io, derived from BepiColombo’s Mercury Radiometer and Thermal Infrared Spectrometer (MERTIS). TMAP has three detectors with a beam split at image plane level: a multispectral imager using an uncooled microbolometer and two radiometer line detectors provide greater precision than the imager for background temperatures (80–150 K) as well as a precise temperatures measurement of active lava flows at 2μm. The TMAP microbolometer and radiometer operate primarily in a pushbroom imaging configuration. The optical design of TMAP is simplified from MERTIS, replacing the spectrometer with simple stripe filters on the microbolometer. Minor modifications of the three-mirror anastigmat (TMA) telescope optics and updating the microbolometer improve the spatial resolution by over 5x. TMAP has a fully reflective, gold-coated F/2.5 TMA optical path with 135-mm focal length. A flip-panel in the optical path between the detectors and mirror 3 serves as a calibration target and follows the standard design used in a wide range of flight instruments. TMAP will measure thermal infrared emission of SO2-free areas of silicate to characterize spectral shape and locate the Christiansen feature emissivity maximum with 8 stripe filters spanning 4.5–16 μm. TMAP will classify eruptions over a significant portion of Io using a 2μm filter on the radiometer and two 5μm bands of the bolometer. TMAP will measure the surface radiance both with the microbolometer between 5 and 16 μm and with the radiometer at wavelength ≥18μm.
Diffractive Optical Elements (DOEs) are commonly used in the photonics community for several purposes, such as geometrical calibration of cameras,1 medical treatments, lithography, LIDAR applications. In the context of the optical alignment and integration of the RAman Spectrometer for MMX (RAX),2 a DOE was included in the test setup with the goal of providing a clear figure of merit to optimize the focusing of a dioptric lens objective on to the spectrometer detector. This Raman spectrometer will be integrated later this year in a small Rover on-board the Martian Moons eXploration (MMX) mission led by JAXA, and will operate on Phobos’ surface to characterize the different materials composing Phobos’ soil. To achieve this, the optical design of RAX is very challenging in terms of performance to reach in very limited volume and mass. As described in Ref. 2, the optical alignment and integration of RAX was a very challenging exercise, requiring several optical setups and methods. The usage of a DOE was introduced to solve a classical problem during the integration of a camera: how to integrate both the optical objective (lens assembly) and the detector to ensure that both the optical focal plane and the detector sensitive plane are co-planar. When illuminated by a collimated laser beam, the implemented DOE generates a regular pattern of collimated beams with well-known deviation angles from the input beam. It acts as a 2D diffraction grating, and generates a pattern field which covers the entire field of view of our camera. Thanks to this property, the Camera Interface Objective of RAX could be successfully positioned and oriented with respect to the detector mechanical interface. It was achieved by acquiring successive images of the DOE pattern with controlled defocused laser beam illuminating it. We were then able to compute the equivalent mechanical defocus needed to maximize the image quality. This maximizes the overall instrument performance and will ensure best possible scientific measurement on Phobos.
The Martian Moons eXploration (MMX) mission led by JAXA to Mars moons Phobos and Deimos involves a small rover developed by DLR/CNES that will be operating on Phobos’ surface. Aboard it is the Raman Spectrometer for MMX (RAX), whose main scientific objectives address Phobos surface mineralogy, its heterogeneity and relation to the Mars mineralogy. Raman spectrometers require strong suppression of straylight, since this technique operates with few nano-Watt signals that should have significant contrast to all other sources of light inside the instrument. The mission requirements involving RAX call for a compact and sophisticated optical design, precluding space for straylight suppressive elements. To optimize straylight suppression in RAX, Raman scattering, Photoluminescence and reflection were characterized for candidate coatings representing different absorbing materials and fabrication technologies over spectral ranges between 530 nm and 680 nm. This was complimented by mechanical testing to aid selection of the coatings for parts inside the RAX flight model.
PLATO (PLAnetary Transits and Oscillations) mission is a space-based optical multi-camera photometer mission of the European Space Agency to identify and characterize exoplanets and their hosting stars using two main techniques: planetary transit and asteroseismology.
The PLATO spacecraft is composed of a Service Module and a Payload Module. The Service Module comprises all the conventional spacecraft subsystems and the sun shield with attached solar arrays. The Payload Module consists of a highly stable optical bench, equipped with 26 optical imagers/cameras covering a global field of view of > 2232 deg2. The design includes two types of cameras: 24 Normal Cameras (N-CAMs) with measurement cadences of 25s and 2 Fast Cameras (F-CAMs) with a cadence of 2.5s. The PLATO spacecraft data is complemented by ground based observations and processed by a dedicate Science Ground Segment.
We describe the mission and spacecraft architecture and provide a view of the current status of development.
PLATO (PLAnetary Transits and Oscillations of stars) is a European Space Agency medium class mission, whose launch is foreseen for 2026. Its primary goal is to discover and characterise terrestrial exoplanets orbiting the habitable zone of their host stars. This goal will be reached with a set of 26 wide field-of-view cameras mounted on a common optical bench. Here we show some results of the first cryogenic vacuum test campaign made on the Engineering Model (EM) of one PLATO camera, performed at the Netherlands Institute for Space Research (SRON). In particular we present the search for the best focus temperature, which was done first by using a Hartmann mask, and then by maximizing the ensquared energy fractions of the point spread functions (PSFs) on the entire field of view taken at different temperature plateaus. Furthermore we present the PSF properties of the EM at the nominal focus temperature over all the field of view, focusing on the ensquared energy fractions. The Engineering Model camera was successfully integrated and validated under cryo-vacuum tests, allowing the mission to pass ESA’s Critical Milestone, and confirming the mission is on track for launch in 2026.
The PLAnetary Transits and Oscillations of stars mission (PLATO) is the M3 mission in ESA’s Cosmic Vision 2015-2025 Programme, see Rauer et al. (2014).1 The PLATO mission aims at detecting and characterizing extrasolar planetary systems, including terrestrial exoplanets around bright solar-type stars up to the habitable zone. To be able to perform the required high precision photometric monitoring of the large target stars sample, PLATO is based on a multi-telescope configuration consisting of 26 Cameras, so as to provide simultaneously a large field of view and a large collecting aperture. The optical design is identical for all cameras and consists of a 6-lens dioptric design with a 120 mm entrance pupil and an effective field of view of more than 1000 square degrees. As for every optical system, especially dioptric ones, the presence of optical ghosts can dramatically affect the scientific observations. Thanks to the application of an excellent anti-reflection coating, PLATO’s cameras are by design very insensitive to ghosts. However, the residual faint back reflections focused on the detectors have to be simulated and considered during science operation (target selection) and in data correction algorithms. This article describes the different optical analyses performed to estimate the importance of ghosts in PLATO’s cameras, as well as the simulations performed to support the preparation of the test campaign on the first PLATO camera: the engineering model. Finally, the test execution, data analysis and results are presented and compared to the simulated data.
PLATO is an exoplanet hunting mission of the European Space Agency. It is a medium-class mission, with a launch foreseen in 2026. Its prime objective is to uncover Earth-sized planets residing in their habitable zone. The payload consists in 26 cameras with a very wide field of view. These cameras consist in a Telescope Optical Unit, aligned at ambient and characterised at the operational temperature, and a Focal Plane Array bearing the detectors, and delivered after coupling with the Front End Electronics. In this contribution, we report on the alignment of the Engineering Model camera of Plato, i.e., the input metrology, the mechanical alignment of the optical unit with the focal plane array, the test environment and the optical characterisation throughout the process until the integrity check after delivery to the cryo-vacuum testing facility where the camera underwent a thorough performance demonstration. We also give a detailed description of the bolting process and the associated error budget.
The Martian Moons eXploration (MMX) mission led by JAXA will conduct remote sensing of both Martian moons Phobos and Deimos and in-situ observations and return samples from Phobos. A small rover will be operating on Phobos’ surface and perform scientific measurements, in particular with its Raman Spectrometer for MMX (RAX). The instrument is jointly developed by DLR with partners from Spain (INTA, University of Valladolid) and Japan (JAXA, University of Tokyo). With its more than 20 optical elements (e.g. laser, lenses, mirrors, grating, dichroic beam-splitters, spectral filters), the optical alignment and integration of this very compact Raman spectrometer was one of the biggest challenges of the instrument development at DLR. This article will cover the different steps of alignment with 1) the integration of the lenses in each individual lens group, 2) the alignment and integration of each lens group to build the spectrometer, and 3) the global alignment verification of the end-to-end instrument. The main goal was to integrate the optical elements in RAX’s mechanical housing providing maximized scientific performance. This meant for example that the detector’s sensitive surface had to be precisely placed at the focal plane surface of the imaging objective to optimize the spectral resolution, but also that the confocality of the laser output (and image on Phobos’ surface) with the spectrometer slit had to be very accurately adjusted to optimize the Signal to Noise Ratio of the Raman features. Aligning and integrating a state-of-the art Raman spectrometer in a very compact volume of less than 10x10x10 cm³ and a mass lower than 1.5 kg was challenging but successful. The different tests performed on the instrument presented here also showed the robustness of the design and demonstrated that RAX can perform excellent scientific measurements on Phobos.
Verification of thermal-mechanical-optical design for optical instruments in space exploration is highly significant due to large temperature variation and exposure to high shock and vibration levels. Such instruments must be completely robust to these harsh environments, as there are usually no options for realignment. The JAXA Martian Moons eXploration (MMX) Mission is set for launch in 2024 with main objectives to study the Martian moons, Deimos and Phobos. A rover will acquire for the first time Raman spectra of the Phobos surface using the Raman Spectrometer for MMX (RAX) developed at DLR. The Structural-Thermal-Model (STM) of RAX presented an early opportunity to evaluate the robustness of the instrument optical alignment to thermal and mechanical environments. An interferometric method implementing dummy objectives with cross hairs was developed to enable inline six-DOF measurements at critical places within the STM before development model (DM) optics were manufactured.
The PLAnetary Transits and Oscillations of stars mission (PLATO) is the M3 mission in ESA’s Cosmic Vision 2015-2025 Programme, see Rauer et al. (2014).1 The PLATO mission aims at detecting and characterizing extrasolar planetary systems, including terrestrial exoplanets around bright solar-type stars in the habitable zone. In order to achieve its scientific objectives, PLATO must perform uninterrupted high precision photometric monitoring of large samples of stars during long periods to detect and characterize planetary transits. The scientific payload of PLATO, developed and provided by the PLATO Mission Consortium (PMC) and ESA, is based on a multi-telescope configuration consisting of 24 “Normal” (N) cameras and 2 “Fast” (F) cameras, so as to provide simultaneously a large field of view and a large collecting aperture. The optical design is identical for all cameras and consists of a 6-lens dioptric design with a 120 mm entrance pupil and an effective field of view of more than 1000 deg2. This concept results in an overall field-of-view of more than 2000 deg², spread over 104 CCDs of 20 mega-pixels each. Associated to very accurate pointing and alignment requirements, this is a real challenge to define and breakdown precise specifications to several sub-systems in order to ensure that this overall field of view budget is achieved and verified. We propose to go through the budget that was performed for the PLATO camera and to describe how we intend to satisfy this scientific requirement. To make it more challenging, it has to be taken into account that the PLATO spacecraft will have to rotate of 90° every three months without changing its field of view (due to its orbit in L2 and the sun illumination limitations). This has to be considered in the breakdown of the budget and design of all sub-systems. A consequence of this large field of view is the difficulty to reach very good and harmonious optical performances across the field, and in a realistic depth of focus. Therefore, the focusing budget is also very challenging for the development of the PLATO cameras. We will describe the way the PLATO’s camera focusing budget has been broken down into allocations and how it is planned to be verified. To ensure optimal performances in-flight, the PLATO cameras have the extraordinary capabilities to perform re-focusing using a high precision Thermal Control System (TCS). Each individual camera on the payload can be thermally controlled independently from its neighbor to reach its own optimal operational temperature. The different consequences of this concept into the budget allocations and sub-system development will be discussed.
The PLAnetary Transits and Oscillations of stars mission (PLATO) is the M3 mission in ESA’s Cosmic Vision 2015-2025 Programme. The PLATO mission aims at detecting and characterizing extrasolar planetary systems, including terrestrial exoplanets around bright solar-type stars in the habitable zone. In order to achieve its scientific objectives, PLATO must perform uninterrupted high precision photometric monitoring of large samples of stars during long periods to detect and characterize planetary transits. The PLATO light curves will also contain information on the seismic activity of the stars, which will lead to the determination of radii and ages of parent stars. The scientific payload of PLATO, developed and provided by the PLATO Mission Consortium (PMC), is based on a multi-telescope configuration consisting of 24 “Normal” (N) cameras and 2 “Fast” (F) cameras, so as to provide simultaneously a large field of view and a large collecting aperture. The optical design is identical for all cameras and consists of a 6-lens dioptric design with a 120 mm entrance pupil and an effective field of view of more than 1000 deg2. The calibration and characterization of PLATO’s cameras is a real challenge, especially in terms of quantities: there are 24 FMs + 2 Flight Spares + 2 Qualification Models and finally 1 EM to calibrate. In this context, the on-ground calibration and characterization plan of the cameras was developed to the strict minimum needed. This means that all the measurements that can be performed in-orbit will not be calibrated on-ground. Our aim is to give an overview of the on-ground activities planned in the coming years to calibrate, characterize and verify the PLATO’s cameras, both in terms of organization and technical solutions. In particular, a detailed description of the geometric calibration used for the Fine Guidance System (FGS) and the focusing calibration will be given. PLATO’s Cameras have indeed the unusual but powerful feature to use a temperature control system to refine their focus. A description of the in-flight calibration plan (including for example the repetition of the focusing calibration, the micro-scanning procedure to determine high-resolution PSFs) will then be given to get the full overview of the calibration, characterization and verification of PLATO’s cameras. Calibrating and verify so many cameras in space, without any calibration targets/sources on board, only using pointing capabilities of the satellite, stellar targets and advanced data processing is a real challenge for this mission. A particular attention will be given to the micro-scanning procedure and inversion techniques required for precise PSF Modelling.
PLATO is an exoplanet hunting mission from the European Space Agency. It is a medium-class mission, with a launch foreseen in 2026. Its prime objective is to uncover Earth-sized planets residing in the habitable zone of their host star. The payload consists of 26 cameras with a very wide field-of-view. While the operational temperature of the cameras will be -80°C, the focal plane of each camera will be integrated with its telescope assembly (bearing the optics) at room temperature. The degradation of the optical quality at ambient, combined with the detector dark current and with the very high accuracy required from the alignment process bring a number of interesting challenges. In the present article, we review the alignment concept, present optical simulations of the measurements at ambient along with their analysis, and present an error budget for the optical measurements. The derivation of this error budget is easily applicable to all optical measurements to be performed during the alignment, i.e. the definition of the best image plane at the operational temperature and the optical alignment itself, at room temperature.
High-resolution spectropolarimetry is a technique used to study many astronomical objects including stellar magnetic fields. It has mainly been used on ground for optical and, more recently, infrared (IR) observations. Space mission projects including ultra-violet (UV) high-resolution spectropolarimetry, such as Pollux onboard LUVOIR proposed to NASA, are being studied in Europe under CNES leadership. Bringing a spectropolarimeter into space means that the instrument should be prepared for space environment including temperatures. The UV polarimeter we are considering is composed by a rotating modulator and an analyzer. Both components are made of magnesium fluoride (MgF2). The modulator is a rotating block of waveplates in molecular adhesion, each plate having its own fast axis. The analyzer is a Wollaston prism, also made with molecular adhesion. MgF2 being birefringent, the plates and prism are anisotropic and will dilate and retract due to thermal changes differently along their fast and slow axes. Each plate having its own fast axis, the thermal changes will create stress at the interfaces, i.e. at the molecular adhesion between the plates. This study focuses on the most critical part: the plates of the modulator. To demonstrate the resistance of the modulator and increase its technological readiness level (TRL), an optical bench including interferometry has been set at the Paris Observatory. It allows us to observe in real time the state of the molecular adhesion between plates as they are submitted to thermal changes in a vacuum chamber. Additional samples have been tested in a thermal vacuum chamber at CNES. This article describes the modulator using molecular adhesion, the test experiments, and the conclusion of this thermal study. Although molecular adhesion broke in 2 samples during thermal cycling, most samples survived which provides encouraging results for this technique.
High-resolution spectropolarimetry is a useful astronomical technique, in particular to study stellar magnetic fields. It has been extensively used in the past but mostly in the visible range. Space missions equipped with high-resolution spectropolarimeters working in the ultra-violet (UV) are now being studied. We propose a concept of a polarimeter working with temporal modulation and allowing to perform Stokes IQUV measurements over the full UV + Visible range. The purpose of this article is to describe the polarimeter concept, two prototypes and the bench developed to perform on ground testing to establish the performances of this new polarimeter.
PLATO (PLAnetary Transits and Oscillation of stars) is the ESA Medium size dedicated to exo-planets discovery, adopted in the framework of the Cosmic Vision program. The PLATO launch is planned in 2026 and the mission will last at least 4 years in the Lagrangian point L2. The primary scientific goal of PLATO is to discover and characterize a large amount of exo-planets hosted by bright nearby stars, constraining with unprecedented precision their radii by mean of transits technique and the age of the stars through by asteroseismology. By coupling the radius information with the mass knowledge, provided by a dedicated ground-based spectroscopy radial velocity measurements campaign, it would be possible to determine the planet density. Ultimately, PLATO will deliver the largest samples ever of well characterized exo-planets, discriminating among their ‘zoology’. The large amount of required bright stars can be achieved by a relatively small aperture telescope (about 1 meter class) with a wide Field of View (about 1000 square degrees). The PLATO strategy is to split the collecting area into 24 identical 120 mm aperture diameter fully refractive cameras with partially overlapped Field of View delivering an overall instantaneous sky covered area of about 2232 square degrees. The opto-mechanical sub-system of each camera, namely Telescope Optical Unit, is basically composed by a 6 lenses fully refractive optical system, presenting one aspheric surface on the front lens, and by a mechanical structure made in AlBeMet.
The space mission Arago is proposed as a candidate to ESA’s Cosmic Vision M5 call by the UVMag consortium. Arago is dedicated to the study of the dynamic 3D environment of stars and planets. Thanks to a high-resolution UV and visible spectropolarimeter, the instrument will detect and characterize the magnetic fields of the stars, their environment and its impact on exoplanets. Scientific requirements impose a wide spectral range from 119 to 888 nm with a single full-Stokes polarimeter followed by two high-resolution spectrographs. To achieve these stringent specifications, a polychromatic concept of polarimeter has been studied and tested thanks to a R and T study funded by CNES. Using an optimized combination of Magnesium Fluoride plates followed by a polarization analyzer, it measures all four Stokes parameters with a constant efficiency over the spectral range. This is performed with a sequence of 6 sub-exposures acquired with different plate angles. The two orthogonal polarized beams coming out of the polarimeter feed two spectrographs. The UV spectrograph has a spectral resolution of at least 25000 over its spectral range, while the visible spectrograph works at least at 35000. Finally, to image the high-resolution spectra, a CCD detector and a MCP were chosen for the visible and UV arms of the instrument respectively.
This paper describes the complete optical design of Arago’s instrument, as proposed to ESA as an answer to its M5 call, from the 1.3-m diameter telescope to the detectors. The design of the polarimeter is presented as well as the unusual way of demodulating the polarization information, in order to have a polychromatic polarimeter working with the same efficiency from FUV to NIR. The optical design of the UV and visible échelle spectrographs and their detection chains are also presented, as well as the achieved performances.
The UVMag consortium will propose the Arago space mission to the ESA call Cosmic Vision M5. This mission aims at characterizing all kind of stars and their environment simultaneously, to better understand the cycle of matter in our galaxy. It carries a single instrument, a spectropolarimeter, acquiring data from 119 to 888 nm and enabling the determination of the magnetic field of stars thanks to the Zeeman effect. One of the key instrumental point of this project is the development of an efficient polarimeter over the large spectral range and in space. We chose to use a polychromatic temporal modulation to achieve a measurement of all four Stokes parameters: I the intensity, Q and U the linear polarization states, and V the circular polarization. The modulator is composed by several birefringent Magnesium Fluoride plates, optimized to achromatize the extraction efficiency of the Stokes parameters from the FUV to the NIR. This polarization modulator is followed by a polarization beam-splitter to analyze the state of the light. After the polarization analysis, the light goes through a high-resolution spectrograph. We present the theoretical optimization and design of the polarimeter and of the whole instrument, as well as the first laboratory results on this concept.
Developing an efficient and robust polarimeter for wide spectral ranges and space applications is a main issue in many projects. As part of the UVMag consortium created to develop UV facilities in space (e.g. the Arago mission proposed to ESA), we are studying an innovative concept of polarimeter that is robust, simple, and efficient on a wide spectral range. The idea, based on the article by Sparks et al. (2012), is to use polarization scramblers to create a spatial modulation of the polarization. Along the height of the wedges of the scramblers, the thickness of the birefringent material crossed by the light, and thus the retardance, vary continuously. This variation creates an intensity modulation of the light related to the entrance polarization state. Analyzing this modulation with a linear polarizer, and dispersing the light spectrally in the orthogonal spatial direction, enables the measurement of the full Stokes vector over the entire spectrum. This determination is performed with a single-shot measurement and without any moving parts in the system.
After a quick introduction to the concept and optical design, this article presents the tolerancing study of the optical bench using this spectropolarimeter. The impact of different error sources, such as, birefringence uncertainty or decenter of the wedges, is investigated.
UVMag is a project of a space mission equipped with a high-resolution spectropolarimeter working in the UV and visible range. This M-size mission will be proposed to ESA at its M4 call. The main goal of UVMag is to measure the magnetic fields, winds and environment of all types of stars to reach a better understanding of stellar formation and evolution and of the impact of stellar environment on the surrounding planets. The groundbreaking combination of UV and visible spectropolarimetric observations will allow the scientists to study the stellar surface and its environment simultaneously. The instrumental challenge for this mission is to design a high-resolution space spectropolarimeter measuring the full- Stokes vector of the observed star in a huge spectral domain from 117 nm to 870 nm. This spectral range is the main difficulty because of the dispersion of the optical elements and of birefringence issues in the FUV. As the instrument will be launched into space, the polarimetric module has to be robust and therefore use if possible only static elements. This article presents the different design possibilities for the polarimeter at this point of the project.
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