Since 1999, MERSEN BOOSTEC designs, manufactures and sells products made of sintered silicon carbide (SiC) mainly for space applications. Improvement of the state of surface of SiC substrates is essential to reduce scattering losses. In collaboration with CNES, a comparative study of microstructural, mechanical, and optical performances of different ceramic processes has been involved to optimized SiC substrates. Then, the comparative study has been extended to scattering losses in collaboration with the Institut FRESNEL which is expert in light scattering metrology. Comparative measurements on the developed substrates have been performed on Spectrally and Angularly resolved Light Scattering characterisation Apparatus (SALSA). This communication will present the results of this study which are already very promising for the development of the next generation SiC optics.
Luc Damé, Eleanore Fringhian rupert, Patrick Lacroix, Pierre Gilbert, Nicolas Caignard, Mustapha Meftah, Nicolas Rouanet, Pierre Etcheto, Jacques Berthon
SUAVE (Solar Ultraviolet Advanced Variability Experiment) is a far UV imaging solar telescope (Lyman Alpha, 121.6 nm, Herzberg continuum, 200-242 nm, etc.) of novel design for ultimate thermal stability and long lasting performances over several years instead of, often, a few weeks or months in this wavelength range. SUAVE is a 80 mm Ritchey-Chrétien off-axis telescope with "mushroom type" SiC mirrors and no entrance window for long and uncompromising observations in the UV (no coatings of mirrors, flux limited to less than 2 solar constants on filters to avoid their degradation), associated with an ultimate thermal control (no central obscuration resulting in limited thermal gradients and easier heat evacuation, focus control, stabilization). Design and performances will be detailed as well as results of thermal/optical tests performed on the SiC primary mirror and its regulated support plate also in SiC. Plans for the realization of a representative breadboard for testing of both optical and thermal properties are presented. SUAVE is the main instrument of the Solar/Climate microsatellite SoSWEET mission (Solar ultraviolet variability and Space Weather Extreme EvenTs).
This conference presentation was prepared for the Space Telescopes and Instrumentation 2022: Ultraviolet to Gamma Ray conference at SPIE Astronomical Telescopes + Instrumentation, 2022.
SUAVE (Solar Ultraviolet Advanced Variability Experiment) is a far UV imaging solar telescope (Lyman Alpha, 121.6 nm, Herzberg continuum, 200-242 nm, etc.) of novel design (off-axis telescope with "mushroom type" SiC mirrors) for ultimate thermal stability and long lasting performances over years instead of, often, a few weeks or months in this wavelength range. SUAVE has no entrance window for long and uncompromising observations in the UV (no coatings of mirrors, flux limited to less than 2 solar constants on filters to avoid their degradation), associated with an ultimate thermal control (no central obscuration resulting in limited thermal gradients and easier heat evacuation, focus control, stabilization). Design and anticipated performances will be detailed as well as results of representative thermal/optical tests performed on the SiC primary mirror and support regulated plate (SiC also). SUAVE is the main instrument of the Solar/Climate SoSWEET-SOUP constellation mission.
PILOT (Polarized Instrument for Long wavelength Observations of the Tenuous interstellar medium) is a balloonborne astronomy experiment designed to study the polarization of dust emission in the diffuse interstellar medium in our Galaxy. The PILOT instrument allows observations at wavelengths 240 μm and 550 μm with an angular resolution of about two arcminutes. The observations performed during the two first flights performed from Timmins, Ontario Canada, and from Alice-springs, Australia, respectively in September 2015 and in April 2017 have demonstrated the good performances of the instrument. Pilot optics is composed of an off axis Gregorian type telescope combined with a refractive re-imager system. All optical elements, except the primary mirror, which is at ambient temperature, are inside a cryostat and cooled down to 3K. The whole optical system is aligned on ground at room temperature using dedicated means and procedures in order to keep the tight requirements on the focus position and ensure the instrument optical performances during the various phases of a flight. We’ll present the optical performances and the firsts results obtained during the two first flight campaigns. The talk describes the system analysis, the alignment methods, and finally the inflight performances.
SUAVE (Solar Ultraviolet Advanced Variability Experiment) is a far UV imaging solar telescope (Lyman Alpha, 121.6 nm, Herzberg continuum, 200-220 nm, etc.) of novel design for ultimate thermal stability and long lasting performances. SUAVE is a 80 mm Ritchey-Chrétien off-axis telescope with SiC mirrors and no entrance window for long and uncompromised observations in the UV (no coatings of mirrors, flux limited to less than 2 solar constants on filters to avoid degradation), associated with an ultimate thermal control (no central obscuration resulting in limited thermal gradients and easier heat evacuation, focus control, stabilization). Design and anticipated performances will be detailed as well as the realization process under way. Tests on a representative breadboard will be performed in 2018 (CNES R&T). SUAVE is the main instrument of the SUITS/SWUSV (Solar Ultraviolet Influence on Troposphere/Stratosphere / Space Weather and Ultraviolet Solar Variability) microsatellite mission.
Control stray light is very important in space industry. Indeed, it is one of the main factors in the decreasing of the signal-to-noise and the contrast. Stray light is generally caused by scattered light and ghost images. The Bidirectional Scatter Distribution function (BSDF) measurements allow the quantification of the scattered light by an optical element and becomes an important data to take into consideration when designing telescopes. Standard BSDF measurement goniophotometers often have a resolution of about 0.1° and are mainly working in or close to the visible spectrum. This resolution is far too loose to characterize ultra-polished surfaces. Besides, wavelength range of BSDF measurements for space projects needs to be done far from visible range. How can we measure BSDF of ultra-polished surfaces and diffraction gratings in the UV and IR range with high resolution? We worked on developing a new goniophometer bench in order to be able to characterize scattering of ultra-polished surfaces and diffraction gratings used in everyday space applications. This ten meters long bench was developed using a collimated beam approach as opposed to goniophotometer using focused beam. Sources used for IR characterization were CO2 (10.6μm) and Helium Neon (3.39μm) lasers. Regarding UV sources, a collimated and spatially filtered UV LED was used. The detection was ensure by a photomultiplier coupled with synchronous detection as well as a MCT InSb detector. The so-built BSDF measurement instrument allowed us to measure BSDF of ultra-polished surfaces as well as diffraction gratings with an angular resolution of 0.02° and a dynamic of 1013 in the visible range. In IR as well as in UV we manage to get 109 with same angular resolution of 0.02°. The 1m arm and translation stages allows us to measure samples up to 200mm. Thanks to such a device allowing ultra-polished materials as well as diffraction gratings scattering characterization, it is possible to implement those BSDF measurements into simulation software and predict stray light issues. This is a big help for space industry engineers to apprehend stray light due to surface finishes and to delete those effects before the whole project is done. We are now thinking of possible improvement on our optical bench to try to get dynamic in IR and UV similar to what we have in visible range (e.g. 1013).
This paper, “Presentation du banc de diffusiometrie optique CNES," was presented as part of International Conference on Space Optics—ICSO 1997, held in Toulouse, France.
This paper, “Microfabrication of high performance optical diaphragm by plasma ion beam etching technology," was presented as part of International Conference on Space Optics—ICSO 1997, held in Toulouse, France.
This paper, “Maquette fonctlonnelle optique développée dans le cadre du développement exploratoire nouveau télescope," was presented as part of International Conference on Space Optics—ICSO 1997, held in Toulouse, France.
This paper, “Fond de ciel stratosphérique mesure par le senseur stellaire de PRONAOS," was presented as part of International Conference on Space Optics—ICSO 1997, held in Toulouse, France.
Nicolas Rouanet, Carole Gouvret, Christian Buil, Pierre Etcheto, Jean-Luc Maria, Jean-Jacques Correia, Jean-Pierre Goutail, François Leblanc, Eric Quémerais, Philippe-Jean Hébert, Eric Chassefiere
PHEBUS (Probing of Hermean Exosphere by Ultraviolet Spectroscopy) consists of an ultraviolet spectrometer for the MPO (Mercury Planetary Orbiter) of the Bepi-Colombo Mission.
The goal of this instrument is to detect emission lines of Mercury exosphere in the bandwidth from 55 to 315 nm by recording full spectra. This instrument is made of an entrance mobile baffle, which is necessary to scan vertically the Mercury atmosphere, an off-axis mirror entrance, a slit, two gratings and two detectors. A few different designs, simulated by optical software, are analysed in this paper. They provide essential results as the instrument spectral resolution. Besides a radiometric model is established to observe the spectra we would obtain on the detectors.
The PICARD space borne instrument observes the Sun from far UV to visible wavelengths. Very high geometrical and radiometric accuracy is required to measure the Sun's local diameter. Thus this instrument is very sensitive to stray light. Multiple reflections between the detector, the mirrors and the filters have been modelled with ASAP 6. They are not very critical for a point source, but for a broad source they add a notable contribution, biasing the edge of the Sun image. Near specular scatter from optics also enlarges the instrumental response, especially at short wavelengths. Scatter from baffles and structures is less critical, but the later need a careful design. To fulfil the mission, stay light shall be predicted very accurately, based on measured data, then taken into account in the image processing. Accuracy depends on the model sampling, the reflectivity and contamination of optics, and the misalignments of the filter wheels.
In the context of Research and Technology (R&T), studies have been performed on the coatings of vane edge in the 0.4 to 1 μm spectral range. The main purposes of the study were to improve the diffusing black coatings available on the market and to look for other diffusing black coatings. At the same time, we have also improved the machining technologies of vane edges. The characterisation (thermal tests, radiometric measurements, adhesion tests) of the most promising technologies has been carried out. The results have pointed out the stainless steel vanes with the edge obtained by polishing or by advanced grinding.
Due to more and more stringent requirements for observation missions, diameter of primary mirrors for space telescopes is increasing. Difficulty is then to have a design stiff enough to be able to withstand launch loads and keep a reasonable mass while providing high opto-mechanical performance. Among the possible solutions, Thales Alenia Space France has investigated optimization of ZERODUR mirrors. Indeed this material, although fragile, is very well mastered and its characteristics well known. Moreover, its thermo-elastic properties (almost null CTE) is unequalled yet, in particular at ambient temperature. Finally, this material can be polished down to very low roughness without any coating. Light-weighting can be achieved by two different means : either optimizing manufacturing parameters or optimizing design (or both). Manufacturing parameters such as walls and optical face thickness have been improved and tested on representative breadboards defined on the basis of SAGEM-REOSC and Thales Alenia Space France expertise and realized by SAGEM-REOSC. In the frame of CNES Research and Technology activities, specific mass has been decreased down to 36 kg/m2. Moreover SNAP study dealt with a 2 m diameter primary mirror. Design has been optimized by Thales Alenia Space France while using classical manufacturing parameters – thus ensuring feasibility and costs. Mass was decreased down to 60 kg/m2 for a gravity effect of 52 nm. It is thus demonstrated that high opto-mechanical performance can be guaranteed with large highly lightweighted ZERODUR mirrors.
Since 2007 Sodern has successfully developed visible and near infrared multispectral filter assemblies for Earth remote sensing imagers. Filter assembly is manufactured by assembling several sliced filter elements (so-called strips), each corresponding to one spectral band. These strips are cut from wafers using a two dimensional accuracy precision process.
In the frame of a 2011 R&T preparatory initiative undertaken by the French agency CNES, the filter assembly concept was adapted by Sodern to the long wave infrared spectral band taken into account the germanium substrate, the multilayer bandpass filters and the F-number of the optics.
Indeed the current trend in space instrumentation toward more compact uncooled infrared radiometer leads to replace the filter wheel with a multispectral filter assembly mounted directly above the micro bolometer window. The filter assembly was customized to fit the bolometer size. For this development activity we consider a ULIS VGA LWIR micro bolometer with 640 by 480 pixels and 25 microns pixel pitch. The feasibility of the concept and the ability to withstand space environment were investigated and demonstrated by bread boarding activities.
The presentation will contain a detailed description of the bolometer and filter assembly design, the stray light modeling analysis assessing the crosstalk between adjacent spectral bands and the results of the manufacturing and environmental tests (damp heat and thermal vacuum cycling).
Stray light is an important issue in optical systems and may be responsible for huge limitation of final performances. Use of black coated surfaces is known to be an efficient means to reduce such parasitic light sources and various solutions exist that can be applied to mechanical surfaces such as black paints or black anodization; these coatings are relatively thick and to produce thin, black baffle edges, a thin layer technology is thus needed. In this paper, we show how thin film multilayer coatings can be a solution to answer this problematic as it is possible to design accurate spectral response that present a very low level of reflectance with a zero value of transmittance.
The use of Bidirectional Scatter Distribution Function (BSDF) in space industry and especially when designing telescopes is a key feature. Indeed when speaking about space industry, one can immediately think about stray light issues. Those important phenomena are directly linked to light scattering.
Standard BSDF measurement goniophotometers often have a resolution of about 0.1° and are mainly working in or close to the visible spectrum. This resolution is far too loose to characterize ultra-polished surfaces. Besides, wavelength range of BSDF measurements for space projects needs to be done far from visible range. How can we measure BSDF of ultra-polished surfaces and diffraction gratings in the UV and IR range with high resolution? We worked on developing a new goniophometer bench in order to be able to characterize scattering of ultra-polished surfaces and diffraction gratings used in everyday space applications. This ten meters long bench was developed using a collimated beam approach as opposed to goniophotometer using focused beam. Sources used for IR characterization were CO2 (10.6?m) and Helium Neon (3.39?m) lasers. Regarding UV sources, a collimated and spatially filtered UV LED was used. The detection was ensure by a photomultiplier coupled with synchronous detection as well as a MCT InSb detector.
The so-built BSDF measurement instrument allowed us to measure BSDF of ultra-polished surfaces as well as diffraction gratings with an angular resolution of 0.02° and a dynamic of 1013 in the visible range. In IR as well as in UV we manage to get 109 with same angular resolution of 0.02°. The 1m arm and translation stages allows us to measure samples up to 200mm.
Thanks to such a device allowing ultra-polished materials as well as diffraction gratings scattering characterization, it is possible to implement those BSDF measurements into simulation software and predict stray light issues. This is a big help for space industry engineers to apprehend stray light due to surface finishes and to delete those effects before the whole project is done.
We are now thinking of possible improvement on our optical bench to try to get dynamic in IR and UV similar to what we have in visible range (e.g. 1013).
PILOT (Polarized Instrument for Long wavelength Observations of the Tenuous interstellar medium) is a balloonborne astronomy experiment designed to study the polarization of dust emission in the diffuse interstellar medium in our Galaxy. The PILOT instrument allows observations at wavelengths 240 μm (1.2THz) with an angular resolution about two arc-minutes. The observations performed during the first flight in September 2015 at Timmins, Ontario Canada, have demonstrated the optical performances of the instrument.
Observations in the UV and EUV allow many diagnostics of the outer layers of the stars and the Sun so that more and more space telescopes are developed to operate in this fundamental spectral range. However, absorption by residual contaminants coming from polymers outgassing causes critical effects such as loss of signal, spectral shifts, stray light… Thus, a cleanliness and contamination control plan has to be defined to mitigate the risk of damage of sensitive surfaces. In order to specify acceptable cleanliness levels, it is paramount to improve our knowledge and understanding of contamination effects, especially in the UV/EUV range. Therefore, an experimental study has been carried out in collaboration between CNES and IAS, in the frame of the development of the Extreme UV Imager suite for the ESA Solar Orbiter mission; this instrument consists of two High Resolution Imagers and one Full Sun Imager designed for narrow pass-band EUV imaging of the solar corona, and thus very sensitive to contamination. Here, we describe recent results of performance loss measured on representative optical samples. Six narrow pass-band filters, with a multilayer coating designed to select the solar Lyman Alpha emission ray, were contaminated with different amounts of typical chemical species. The transmittance spectra were measured between 100 and 200 nm under high vacuum on the SOLEIL synchrotron beam line. They were compared before and after contamination, and also after a long exposure of the contaminated area to EUV-visible radiations.
PILOT is a balloon-borne astronomy experiment designed to study the polarization of dust emission in the diffuse
interstellar medium in our Galaxy at wavelengths 240 μm with an angular resolution about two arcminutes. Pilot optics
is composed an off-axis Gregorian type telescope and a refractive re-imager system. All optical elements, except the
primary mirror, are in a cryostat cooled to 3K. We combined the optical, 3D dimensional measurement methods and
thermo-elastic modeling to perform the optical alignment. The talk describes the system analysis, the alignment
procedure, and finally the performances obtained during the first flight in September 2015.
PILOT is a stratospheric experiment designed to measure the polarization of dust FIR emission, towards the diffuse interstellar medium. The first PILOT flight was carried out from Timmins in Ontario-Canada on September 20th 2015. The flight has been part of a launch campaign operated by the CNES, which has allowed to launch 4 experiments, including PILOT. The purpose of this paper is to describe the performance of the instrument in flight and to perform a first comparison with those achieved during ground tests. The analysis of the flight data is on-going, in particular the identification of instrumental systematic effects, the minimization of their impact and the quantification of their remaining effect on the polarization data. At the end of this paper, we shortly illustrate the quality of the scientific observations obtained during this first flight, at the current stage of systematic effect removal.
Multispectral channels are required on many pushbroom optical sensors. A possible technology well suited for focal
plane miniaturization is to assemble several sliced filter elements (so-called stripes), each corresponding to one spectral
channel, and located close to the detectors.
The assembled filter is thus customized to fit detector size. These stripes are cut from a wafer using a two dimensional
accurate process. For the baseline concept, elementary stripes are then cemented edge-to-edge to form a single substrate.
The opaque epoxy used for the stripes assembly creates a light barrier between adjacent elements and thus provides an
interesting solution for cross channel image suppression inside the filter.
This paper recalls the current SODERN's multi-spectral filter assembly status. Since 2007 R&T activity, the feasibility
and the performances have been demonstrated by breadboards and qualification models. The selection of SODERN for
two current VNIR space programs consolidates its role as a leading supplier in this field. A complementary 2011 R&T
study will demonstrate the performances of this technology for the TIR range and the integration on a bolometer.
The PICARD satellite is dedicated to the monitoring of solar activity. It carries several imaging and radiometric
instruments. One of them, SODISM, is a high-resolution radio-imaging telescope measuring the Sun diameter and total
flux in near UV and visible wavelengths. Along with mirrors, SODISM includes highly reflective filters and
attenuators, which generate ghost images. These disturb the Sun edge area, the total flux measurement and also the fine
aiming channel. This is compounded with tilt tolerances, which shift and modify the ghosts images.
Stray light was studied through ASAP simulation, with broad sources and high order splits. Each path was studied
separately, checking its effect on instrument performance and the possible effect of tilts. Some design improvements
allowed to reduce the most critical paths, while others, although relatively intense, stood clear from the critical areas.
However ground tests and flight results show some residual ghosts, which could not be fully suppressed due to
mechanical tolerances. They shall be taken into account by image processing.
Atmospheric sounding requires high-resolution spectrometers, such as Fourier transform interferometers. Classical ones need moving mirrors to scan the spectrum, but static interferometers with stepped mirrors can achieve high resolution in within a narrow spectral band. CNES is developing such an instrument for CO2 flow monitoring. The breadboard includes two stepped mirrors, a separating plate, a double imaging system and a detector array. To simulate the actual instrument response, we developed a physically realistic model of the full optical system with ASAP, a software well suited for broad sources, partial coherence and non-sequential propagation. After checking the theoretical interferogram and the resulting instrument spectral response for a point source, we simulated the effects of field, coherence length and chromatism. Then we studied the complex ghost reflections between the mirrors, the separating plate, the optics and the detector, taking coherence into account. Resulting interferograms and spectra were compared to the nominal ones. It appears that the most critical ghosts are not the most intense but the best focused, especially when interfering with the nominal waves. Scatter is tolerable, as it is incoherent and relatively uniform. These results led to design improvements and alignment requirements on the breadboard. This study illustrates how physical modeling can contribute to the early design of complex, non-imaging systems.
With the 3S program (the French acronym for SPOT System Follow-on), CNES intends to continue the SPOT Earth Observation mission with the purpose of achieving severe costs reduction. This increases the need for new, lighter, more compact technologies for the payload. Therefore, CNES has launched preliminary studies in some critical payload domains. The paper deals with the work done in order to demonstrate the feasibility of a small telescope that can be used onboard a mini-satellite. A Three-Mirror Anastigmat (TMA) telescope breadboard has been manufactured using the same technologies that would be required to provide in-orbit stability. The TMA has excellent image quality over its whole 8.4 X 1.4 degree FOV and an intrinsic compactness that makes it much smaller than its focal length: as a result, the whole telescope weighs about 40 kg. The paper particularly focuses on the telescope design, the alignment method and the optical performance under stable laboratory environment. The behavior of the telescope under space environment is described, as well as the tests conducted to validate the computed optical performance under thermal variations and vibrations conditions.
IASI is an Infrared Atmospheric Sounding Interferometer devoted to the operational meteorology and to atmospheric studies and is to be installed on-board the second ESA Polar Platform called METOP-1; It is planned to be launched in the year 2000. The required operating lifetime is 4 years with a target of 7 years plus 4 years of ground storage. The cold Optical Unit is located at the focal plane of the Michelson Interferometer. This sub-assembly is designed to divide the IR input flux into 3 spectral bands and to focus it on the 3 arrays of detection. It includes a spectral separation using 2 beam splitters dividing the incoming flux into 3 spectral bands which are 3.4 to 5.0 micrometers , 5.0 to 8.26 micrometers and 8.26 to 15.5 micrometers . Each array stands behind an objective and a set of 4 microlenses. This unit defined the aperture and the field of view of the instrument and operates at 100 K with passive cooling. An overall design of the cold box has been performed for the mechanical structure and for the optics taking into account the space requirements. This structure is interfaced with a passive radiator and is illustrated by several figures. A thermal analysis of this unit has been computed to check the thermal gradient by means of a finite-element software involving several thousands of nodes. A specific optical ray tracer delivered the optimization and the tolerancing of the optical design. The results show that, with severe tolerances, the optical losses and cross-talk meet the requirements. The optical diagram has been drawn, as well as the CNES instrument design. Several critical items have been manufactured to check that they can meet the required performance (photoconductive detectors, microlenses, AR coatings, packaging).
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