The Euclid mission, the spacecraft being the essential space element, has been developed to undertake the challenges of investigate the dark energy and dark matter distribution in the Universe. As the launch date is approaching, the telescope and the integrated payload, encompassing the telescope and with the two science instruments attached behind it, have been successfully tested. The telescope alone was tested under ambient conditions, and the integrated payload was tested in vacuum at operational temperature. The extensive test campaign at telescope level confirmed that its optical performance were better than the required levels. The thermal-vacuum test campaign demonstrated the excellent stability of the optical performance of the entire payload module. In addition, other performances of the integrated payload were tested to gather information on the behavior of the payload which will be used for the preparation of the calibrations in-flight.
In broadband dielectric coatings, the wavefront of the reflected wave can change dramatically in a resonance-like manner as a function of wavelength. These wavefront errors can be a significant issue in high precision instruments. In the last years, effort has been undertaken to design and produce coatings to reduce these resonances. However, today there is still limited capability to characterize by measurement the spectral dependence of the wavefront error with high spectral resolution and accuracy. The goal of this paper is to present and analyze a design for a setup to measure the reflected wavefront from a coated flat component with high accuracy as a function of the wavelength. The proposed design is based on a passive system using high-precision off-axis parabolic mirrors. For sensing the wavefront error a Shack-Hartmann sensor is proposed, whose microlens array design is to be modified. According to error analysis and tolerance studies, the setup is capable of measuring wavefront distortion with sub-2 nm RMS accuracy within 510 nm to 950 nm. The angle of incidence and the polarization can also be varied without a loss of accuracy. In order to determine the point spread function (PSF) with high accuracy in addition to the wavefront measurement, the wavefront error of the setup itself needs to be below 50 nm RMS. The tolerancing performed in this study included the light source, shape errors of the mirrors, beam splitter, polarizers, and the sensors. Shape irregularities of the single elements were simulated by Zernike polynomials, and the residual wavefront error of the setup is estimated by Monte Carlo simulations, including uncertainties of the mechanical positioning. From these simulations, specifications for the mirrors have been worked out based on the goal of a system wavefront error lower than 50 nm RMS. The intended broad spectral range makes it challenging to identify a suitable Shack-Hartmann wavefront sensor. Different sensor configurations are evaluated experimentally, and a reproducible wavefront measurement can be achieved by adjusting the focal length of the microlens array. Thereby, the repeatability in wavefront measurements could be reduced from 3 nm to less than 1 nm RMS by modifying the microlens array parameters. Tilting the polarizer and beam splitter by 2° prevents ghost images and multiple reflections in the setup. Finally, considerations about the realization of a suitable reference measurement with an optical flat of sufficient surface quality are presented.
Euclid is the second M-class mission of ESA’s Cosmic Vision Program. It implements a space telescope to be launched at L2. The objective is to characterize the dynamics of the early Universe by using two instruments: the high definition camera VIS (visible instrument) and the spectrophotometer NISP (Near Infrared Spectrometer and Photometer). Light entering Euclid is either reflected toward VIS in the visible band, or transmitted to NISP in the infrared band by a dichroic mirror. In order to guarantee the quality of scientific data delivered by the mission, the knowledge of any chromatic dependence of the optical payload’s Point-Spread function (PSF) is critical. However, previous works showed that complex coatings, such as high-performance dichroic coating, are likely to induce high chromatic variations in reflection, either as a chromatic “Wave-Front-error” (WFE) and/or as inhomogeneous reflectance profile (R), both affecting PSF morphology. In-depth knowledge of the reflected wavefront by the Euclid Dichroic is then necessary in order to calibrate the in-flight Euclid Observations. This work focuses on two aspects. On the one hand, we present an experimental campaign to measure the dichroic WFE and R at any wavelength, incidence, and polarization state, with an extreme precision. This metrology work implements a bench funded by ESA, designed by Imagine Optic Company, and commissioned at LMA. On the other hand we build a numerical model of the dichroic based on these on-ground measurements. By reproducing the experimental optical properties of the dichroic mirror, we ensure the subjacent thinfilms physics at play is well understood, ultimately providing adequate inputs for the in-flight calibration of Euclid with a suitable level of accuracy.
The Euclid mission, of which the spacecraft is the essential space segment, is being developed to undertake the challenges of mapping the dark energy and dark matter distribution in the Universe. As the launch date is approaching (2nd half of 2022), the development of the spacecraft has successfully passed critical milestones with the manufacturing and integration of the telescope, instruments and service module. Each sub-element of the spacecraft has been qualified and their performance assessed. The assembly of the complete payload and spacecraft is currently on-going. The integrated optical performance end to end of the payload module is currently being assessed based on the as-built knowledge of the parts of the telescope and instruments.
Euclid, an ESA mission designed to characterise dark energy and dark matter, passed its Mission Critical Design Review in November 2018. It was demonstrated that the project is ready to start integration and test of the main systems, and that it has the ability to fulfil its top-level mission requirements. In addition, based on the performances at M-CDR, the scientific community has verified that the science requirements can be achieved for the Weak Lensing and Galaxy Clustering dark energy probes, namely a dark energy Figure of Merit of 400 and a 2% accuracy in the growth factor exponent gamma. We present the status of the main elements of the Euclid mission in the light of the demanding high optical performance which is the essential design driver is the to meet the scientific requirements. We include the space segment comprising of a service module and payload module hosting the telescope and its two scientific instruments, and the ground segment, which encompasses the operational and science ground segment. The elements for the scientific success of the mission for a timely release of the data are shortly presented: the processing and calibration of the data, and the design of the sky survey. Euclid is presently on schedule for a launch in September 2022.
The fairing of the launcher selected for the Space Infrared telescope for Cosmology and Astrophysics (SPICA) mission is not compatible with a primary mirror of 3.5m in diameter. Thus three alternative optical designs of the SPICA Telescope Assembly (STA) with a primary mirror of reduced size were defined and their theoretical optical performances assessed. The impact of the size reduction on the STA optical performances was then quantified. Based on the results of the study, we defined a STA optical design optimum in terms of optical performances and of accommodation of instruments in the STA focal surface.
This paper describes the outcome of the ESA contract 20532/06/NL/Sfe entitled “Instrument concepts using dynamic diffraction gratings”. The goal of the project was to study the optical performance of state of the art dynamic diffraction grating technology and identify potential applications for space missions. A dynamic diffraction grating sample was obtained for characterisation and a demonstrator for a compact spectrometer architecture was implemented and tested.
A new class of spectrometer can be designed using programmable components such as MOEMS which enable to tune the beam in spectral width and central wavelength. It becomes possible to propose for space applications a spectrometer with programmable resolution and adjustable spectral bandwidth.
The proposed way to tune the output beam is to use the diffraction effect with the so-called PMDG (Programmable Micro Diffraction Gratings ) diffractive MEMS. In that case, small moving structures can form programmable gratings, diffracting or not the incoming light.
In the proposed concept, the MOEMS is placed in the focal plane of a first diffracting stage (using a grating for instance). With such implementation, the MOEMS component can be used to select some wavelengths (for instance by reflecting them) and to switch-off the others (for instance by diffracting them). A second diffracting stage is used to recombine the beam composed by all the selected wavelengths. It becomes then possible to change and adjust the filter in λ and Δλ.
This type of implementation is very interesting for space applications (Astronomy, Earth observation, planetary observation). Firstly because it becomes possible to tune the filtering function quasi instantaneously. And secondly because the focal plane dimension can be reduced to a single detector (for application without field of view) or to a linear detector instead of a 2D matrix detector (for application with field of view) thanks to a sequential acquisition of the signal.
The special properties of Volume Bragg Gratings (VBGs) make them good candidates for spectrometry applications where high spectral resolution, low level of straylight and low polarisation sensitivity are required. Therefore it is of interest to assess the maturity and suitability of VBGs as enabling technology for future ESA missions with demanding requirements for spectrometry. The VBGs suitability for space application is being investigated in the frame of a project led by CSL and funded by the European Space Agency. The goal of this work is twofold: first the theoretical advantages and drawbacks of VBGs with respect to other technologies with identical functionalities are assessed, and second the performances of VBG samples in a representative space environment are experimentally evaluated. The performances of samples of two VBGs technologies, the Photo-Thermo-Refractive (PTR) glass and the DiChromated Gelatine (DCG), are assessed and compared in the Hα, O2-B and NIR bands. The tests are performed under vacuum condition combined with temperature cycling in the range of 200 K to 300K. A dedicated test bench experiment is designed to evaluate the impact of temperature on the spectral efficiency and to determine the optical wavefront error of the diffracted beam. Furthermore the diffraction efficiency degradation under gamma irradiation is assessed. Finally the straylight, the diffraction efficiency under conical incidence and the polarisation sensitivity is evaluated.
The size and the weight of state of the art spectrometers is a serious issue regarding space applications. SWIFTS (Stationary Wave Integrated Fourier Transform Spectrometer) is a new FTS family without any moving part. This very promising technology is an original way to fully sample the Fourier interferogram obtained in a waveguide by either a reflection (SWIFTS Lippmann) or counter-propagative (SWIFTS Gabor) interference phenomenon. The sampling is simultaneously performed the optical path thanks to "nano-detectors" located in the evanescent field of the waveguide. For instance a 1.7cm long waveguide properly associated to the detector achieves directly a resolution of 0.13cm-1 on a few centimetre long instruments. Here, firstly we present the development status of this new kind of spectrometers and the first results obtained with on going development of spectrometer covering simultaneously the visible domain from 400 to 1000 nm like an Echelle spectrometer. Valuable technologies allows one to extend the concept to various wavelength domains. Secondly, we present the results obtained in the frame of an activity funded by the European Space Agency where several potential applications in space missions have been identified and studied.
KEYWORDS: Systems engineering, Systems modeling, Space operations, Modeling, Galactic astronomy, Control systems, Systems engineering, Systems modeling, Data modeling, Data processing, Atrial fibrillation, Visualization
In the last years, the system engineering field is coming to terms with a paradigm change in the approach for complexity management. Different strategies have been proposed to cope with highly interrelated systems, system of systems and collaborative system engineering have been proposed and a significant effort is being invested into standardization and ontology definition. In particular, Model Based System Engineering (MBSE) intends to introduce methodologies for a systematic system definition, development, validation, deployment, operation and decommission, based on logical and visual relationship mapping, rather than traditional 'document based' information management.
The practical implementation in real large-scale projects is not uniform across fields. In space science missions, the usage has been limited to subsystems or sample projects with modeling being performed 'a-posteriori' in many instances. The main hurdle for the introduction of MBSE practices in new projects is still the difficulty to demonstrate their added value to a project and whether their benefit is commensurate with the level of effort required to put them in place.
In this paper we present the implemented Euclid system modeling activities, and an analysis of the benefits and limitations identified to support in particular requirement break-down and allocation, and verification planning at mission level.
KEYWORDS: Space operations, Galactic astronomy, Spectroscopy, Systems modeling, Databases, Point spread functions, Seaborgium, Data processing, Calibration, Telescopes
ESA's Dark Energy Mission Euclid will map the 3D matter distribution in our Universe using two Dark Energy probes: Weak Lensing (WL) and Galaxy Clustering (GC). The extreme accuracy required for both probes can only be achieved by observing from space in order to limit all observational biases in the measurements of the tracer galaxies. Weak Lensing requires an extremely high precision measurement of galaxy shapes realised with the Visual Imager (VIS) as well as photometric redshift measurements using near-infrared photometry provided by the Near Infrared Spectrometer Photometer (NISP). Galaxy Clustering requires accurate redshifts (Δz/(z+1)<0.1%) of galaxies to be obtained by the NISP Spectrometer.
Performance requirements on spacecraft, telescope assembly, scientific instruments and the ground data-processing have been carefully budgeted to meet the demanding top level science requirements. As part of the mission development, the verification of scientific performances needs mission-level end-to-end analyses in which the Euclid systems are modeled from as-designed to final as-built flight configurations. We present the plan to carry out end-to-end analysis coordinated by the ESA project team with the collaboration of the Euclid Consortium. The plan includes the definition of key performance parameters and their process of verification, the input and output identification and the management of applicable mission configurations in the parameter database.
The challenging constraints imposed on the Euclid telescope imaging performances have driven the design,
manufacturing and characterisation of the multi-layers coatings of the dichroic. Indeed it was found that the coatings
layers thickness inhomogeneity will introduce a wavelength dependent phase-shift resulting in degradation of the image
quality of the telescope. Such changes must be characterized and/or simulated since they could be non-negligible
contributors to the scientific performance accuracy. Several papers on this topic can be found in literature, however the
results can not be applied directly to Euclid’s dichroic coatings. In particular an applicable model of the phase-shift
variation with the wavelength could not be found and was developed. The results achieved with the mathematical
model are compared to experimental results of tests performed on a development prototype of the Euclid’s dichroic.
KEYWORDS: Data processing, Galactic astronomy, Space operations, Telescopes, Point spread functions, K band, Sensors, Image quality, Data archive systems, Calibration
Euclid is a space-based optical/near-infrared survey mission of the European Space Agency (ESA) to investigate the
nature of dark energy, dark matter and gravity by observing the geometry of the Universe and on the formation of
structures over cosmological timescales. Euclid will use two probes of the signature of dark matter and energy: Weak
gravitational Lensing, which requires the measurement of the shape and photometric redshifts of distant galaxies, and
Galaxy Clustering, based on the measurement of the 3-dimensional distribution of galaxies through their spectroscopic
redshifts. The mission is scheduled for launch in 2020 and is designed for 6 years of nominal survey operations. The
Euclid Spacecraft is composed of a Service Module and a Payload Module. The Service Module comprises all the
conventional spacecraft subsystems, the instruments warm electronics units, the sun shield and the solar arrays. In
particular the Service Module provides the extremely challenging pointing accuracy required by the scientific objectives.
The Payload Module consists of a 1.2 m three-mirror Korsch type telescope and of two instruments, the visible imager
and the near-infrared spectro-photometer, both covering a large common field-of-view enabling to survey more than
35% of the entire sky. All sensor data are downlinked using K-band transmission and processed by a dedicated ground
segment for science data processing. The Euclid data and catalogues will be made available to the public at the ESA
Science Data Centre.
KEYWORDS: Space telescopes, Telescopes, Contamination, Mirrors, Sensors, Scattering, Optical components, Photometry, Contamination control, Picture Archiving and Communication System
In the Euclid mission the straylight has been identified at an early stage as the main driver for the final imaging quality of the telescope. The assessment by simulation of the final straylight in the focal plane of both instruments in Euclid’s payload have required a complex workflow involving all stakeholders in the mission, from industry to the scientific community. The straylight is defined as a Normalized Detector Irradiance (NDI) which is a convenient definition tool to separate the contributions of the telescope and of the instruments. The end-to-end straylight of the payload is then simply the sum of the NDIs of the telescope and of each instrument. The NDIs for both instruments are presented in this paper for photometry and spectrometry.
Euclid is an European Space Agency (ESA) mission to map the geometry of the dark Universe. The mission will investigate the distance-redshift relationship and the evolution of cosmic structures. It will achieve this by measuring shapes and redshifts of galaxies and clusters of galaxies out to redshifts ~2, equivalent to 10 billion years back in time. Euclid will make use of two primary cosmological probes, in a wide survey over the full extragalactic sky : the Weak Gravitational Lensing (WL) and Baryon Acoustic Oscillations (BAO). The main goal of the Euclid payload module (PLM) is to provide high quality imaging of galaxies and accurate measurement (less than 0.1%) of galaxies redshift over a large field of view (FoV). The present paper focuses on the telescope of the PLM excluding the instruments. We present a brief introduction to the Euclid PLM system and will report how the constraints of each instrument have driven the definition of the telescope-to-instrument optical interfaces. Furthermore we introduce the description of the telescope optical characteristics and report its nominal performances. Finally, the technical challenges to be faced by ESA’s industrial partners are underlined.
In June 2012, Euclid, ESA's Cosmology mission was approved for implementation. Afterwards the industrial contracts were signed for the payload module and the spacecraft prime, and the mission requirements consolidated. We present the status of the mission in the light of the design solutions adopted by the contractors. The performances of the spacecraft in its operation, the telescope assembly, the scientific instruments as well as the data-processing have been carefully budgeted to meet the demanding scientific requirements. We give an overview of the system and where necessary the key items for the interfaces between the subsystems.
The focal plane array of the Euclid VIS instrument comprises 36 large area, back-illuminated, red-enhanced CCD detectors (designated CCD 273). These CCDs were specified by the Euclid VIS instrument team in close collaboration with ESA and e2v technologies. Prototypes were fabricated and tested through an ESA pre-development activity and the contract to qualify and manufacture flight CCDs is now underway. This paper describes the CCD requirements, the design (and design drivers) for the CCD and package, the current status of the CCD production programme and a summary of key performance measurements.
EChO is an M-class mission candidate within the science program Cosmic Vision 2015-2025 of the European Space
Agency. It was selected in February 2011 to enter an assessment phase (phase 0/A). Following the internal Concurrent
Design Facility study conducted by ESA in June/July 2011, a call for instrument studies was released in September,
resulting in two consortia being selected to study the complete science instrument on board EChO throughout 2012.
Similarly, two parallel competitive industrial studies of the complete mission will end early 2013.
The instrument study focuses on the design and accommodation in the spacecraft of the scientific instrument, a
spectrometer divided into several channels covering the 0.55 to 11 micron (0.4 to 16 micron goal) wave band. It also
includes the design of the active cryogenic chain required to operate the instrument focal plane detectors.
The industrial study focuses on the complete system-level design, including the mission analysis and operations, the
spacecraft design (both service and payload modules) and also programmatic aspects such as risk mitigation, schedule
and cost analyses.
This paper describes the status of the EChO assessment study at the mid-term review (June/July 2012). It includes a short
introduction to the EChO mission, a brief update on recent work by the Science Study Team (SST) to refine the science
requirements, the description of the telescope trade-off and baseline selection, as well as the status of both instrument
consortia and industrial system-level studies.
The special properties of Volume Bragg Gratings (VBGs) make them good candidates for spectrometry applications
where high spectral resolution, low level of straylight and low polarisation sensitivity are required. Therefore it is of
interest to assess the maturity and suitability of VBGs as enabling technology for future ESA missions with demanding
requirements for spectrometry. The VBGs suitability for space application is being investigated in the frame of a project
led by CSL and funded by the European Space Agency. The goal of this work is twofold: first the theoretical advantages
and drawbacks of VBGs with respect to other technologies with identical functionalities are assessed, and second the
performances of VBG samples in a representative space environment are experimentally evaluated.
The performances of samples of two VBGs technologies, the Photo-Thermo-Refractive (PTR) glass and the
DiChromated Gelatine (DCG), are assessed and compared in the Hα, O2-B and NIR bands. The tests are performed
under vacuum condition combined with temperature cycling in the range of 200 K to 300K. A dedicated test bench
experiment is designed to evaluate the impact of temperature on the spectral efficiency and to determine the optical
wavefront error of the diffracted beam. Furthermore the diffraction efficiency degradation under gamma irradiation is
assessed. Finally the straylight, the diffraction efficiency under conical incidence and the polarisation sensitivity is
evaluated.
Periodic single metallic meander structures have been shown to exhibit extraordinary transmission in the visible
frequency domain within a well-defined pass band that can be shifted by geometry variation. Furthermore, meander
structures are not only linear polarizers but also induce phase retardation between s- and p-polarized light. In addition,
they are able to convert the polarization of light due to plasmonic excitations. Those features combined with the
advantages of plasmonic metamaterials in general, such as radiation stability, temperature independence and low weight
make them perfect candidates for optical devices in space instruments. We show analytically and numerically that an
optical depolarizer can be designed by spatially distributing meander structures in a pixel-like fashion and rotating each
element by a random angle. The depolarizing properties of meander structures, indicated by the Mueller matrix elements,
are investigated for various geometrical parameters and can be improved by stacking two meander structures onto each
other. The presented polarization scrambler can be flexibly designed to work anywhere in the visible wavelength range
with a bandwidth of up to 100 THz. Furthermore, the depolarization effect relies on optical activity rather than
scattering. With our preliminary design, we achieve depolarization rates larger than 60% for arbitrarily polarized,
monochromatic or narrow-band light, respectively. One advantage of our concept is the flexibility to tune the
polarization scrambler to a particular optical frequency or functionality. Circularly polarized light (S = [1, 0, 0, ±1]) for
instance could be depolarized by 95% at 600 THz.
The European Space Agency (ESA) in the frame of its General Study Program (GSP) has started to investigate the
opportunity of using metamaterials in space applications. In that context, ESA has initiated two GSP activities which
main objectives are 1) to identify the metamaterials and associated optical properties which could be used to improve in
the future the performances of optical payloads in space missions, 2) to design metamaterial based devices addressing
specific needs in space applications.
The range of functions for metamaterials to be investigated is wide (spectral dispersion, polarisation control, light
absorption, straylight control...) and so is the required spectral range, from 0.4μm to 15μm.
In the frame of these activities several applications have been selected and the designs of metamaterial based devices are
proposed and their performances assessed by simulations.
We are involved with ESA and CNES since several years, in the analysis of space applications using MOEMS
components. A first concept using a Programmable Micro Diffracting Device (PMDG) has been proposed for an
astronomical spectrometer with a small field of view. In this application the introduction of a MOEMS component has
allowed to reduce the focal plane complexity (one mono detector) and to increase the mission adaptability to the target
(programmable mission). An opto mechanical concept has been proposed and first performance assessed.
A second concept has been studied and deals with the use of a MOEMS component to realize an innovative
spectrometer, so-called convolution spectrometer. In the proposed solution, a MOEMS is used to realize a shifting
spectral window (large spectral width) associated to a slight spectral increment. The signal given by the detector being
the convolution between the target spectral density and the spectral window, it is then possible to recover the target
spectral signal by a deconvolution. A breadboard has been developed, and the concept of the convolution spectrometer
has been successfully demonstrated.
Finally, some results of analysis will be also given concerning the use of a DMD for Earth observation associated to a
push broom detection mode and a large field of view.
A new class of spectrometer can be designed using programmable components such as MOEMS which enable to tune
the beam in spectral width and central wavelength. It becomes possible to propose for space applications a spectrometer
with programmable resolution and adjustable spectral bandwidth.
The proposed way to tune the output beam is to use the diffraction effect with the so-called PMDG (Programmable
Micro Diffraction Gratings) diffractive MEMS. In that case, small moving structures can form programmable gratings,
diffracting or not the incoming light.
In the proposed concept, the MOEMS is placed in the focal plane of a first diffracting stage (using a grating for
instance). With such implementation, the MOEMS component can be used to select some wavelengths (for instance by
reflecting them) and to switch-off the others (for instance by diffracting them). A second diffracting stage is used to
recombine the beam composed by all the selected wavelengths. It becomes then possible to change and adjust the filter
in λ and Δλ.
This type of implementation is very interesting for space applications (astronomy, Earth observation, planetary
observation). Firstly because it becomes possible to tune the filtering function quasi instantaneously. And secondly
because the focal plane dimension can be reduced to a single detector (for application without field of view) or to a
linear detector instead of a 2D matrix detector (for application with field of view) thanks to a sequential acquisition of
the signal.
This paper addresses the interferometric measurements performed on PLANCK Secondary reflector-Flight Model (SRFM) during the cryo-optical test at the Centre Spatial de Liege in Belgium. It was requested to measure the changes of the surface figure error (SFE) with respect to the best ellipsoid, between 293 K and 50 K, with a 1 μm RMS accuracy. To achieve this, Infra Red interferometry has been selected and a dedicated thermo mechanical set-up has been constructed. One emphasizes on the solutions adopted to cope with high surface slopes appearing at cryogenic temperature. Indeed, detector resolution has been exploited to resolve high density fringes at the expense of the aperture. A stitching procedure has been implemented to reconstruct the full aperture measurement with success. Test results are presented.
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