The Comet Interceptor mission has been adopted by the European Space Agency (ESA) Science Programme Committee in June 2022 as the first ”F” mission in the Science Programme. The aim of the mission is to increase the knowledge on comets and on the Solar System formation by encountering and exploring a Dynamically New Comet (DNC) or an Interstellar Object (ISO) originating at another star. EnVisS (Entire Visible Sky) is an all-sky camera designed to fly on Comet Interceptor and whose scientific task is to study the radiance and the polarization properties of the comet coma in the visible spectrum. The camera is composed of an optical head, a filter strip assembly and a detector. The Institute for Photonics and Nanotechnologies (CNR-IFN) of Padova and Leonardo SpA (Campi BisenzioFlorence) are in charge of the design of the filter package, which currently consists of three filter strips glued side by side. The central strip is a high transmission broadband (BB) filter in the range 550–800 nm with no polarization properties, while the side ones are linear polarization filters with the same transmission bandpass as the BB and with polarization axis at 45° from one another. In the CNR-IFN laboratories different types of polarizers have been tested to establish which one has the most fitting properties for EnVisS’s purposes. The analyzed filters are Moxtek Visible Light Polarizer RCV8N2EC and Ultra BroadBand Polarizer UBB01A, and Polarcor Wide Band Polarizer. For each type of polarizing filter, both transmissivity and reflectivity have been measured and compared both with those of the other filters as well as data provided by the manufacturer. Overall, measurements of the filters’ transmissivity and reflectivity agree with those provided by the supplier and mostly fit EnVisS’ purposes. Thanks to its optimal performance and the fused silica substrate, Moxtek UBB01A is considered the best candidate filter for the instrument between the polarizers that have been characterized.
In the framework of an ESA space mission, called Comet Interceptor, scheduled for launch in 2029 some polarizers have been tested and characterized. These polarizers are considered for being mounted on the EnVisS (Entire Visible Sky) instrument. EnVisS is a fish-eye camera that will dynamically acquire images of a comet and the surrounding all-sky coma in the visible range exploiting the spacecraft spinning. The spacecraft will perform a fly-by of the comet, venturing very near to its nucleus. Inside the EnVisS instrument, before reaching the sensor, the acquired light will cross one of the 3 selected scientific filters, i.e. one broadband and two polarizers. The determination of the optical properties of these filters is crucial for the correct prediction of the performance of the camera. The Padua branch of the CNR-IFN (Italian National Research Council – Institute for Photonics and Nanotechnologies) has a long experience in metrology for space instrumentation and has developed a laboratory system for reflectance and transmittance optical measurements. The set-up is composed of a broadband light source, a rotator stage for allocating the samples, and a spectrometer. According to the purpose of the measurement, the structure of this setup can be arranged by adding other elements along the ray path. This system allows measuring wavelength dependent transmissivity and reflectivity properties for optical components such as mirrors, lenses and filters in the UV, visible and NIR spectral range. The polarizing filters under selection for the EnVisS instrument are commercially available components based on the wire grid technology. We have measured their optical transmissivity and reflectivity. In this paper, we present the employed instruments, the step-by-step procedure and the results compared to the nominal performance of the polarizers.
Metis is a multi-wavelength coronagraph onboard the European Space Agency (ESA) Solar Orbiter mission. Thanks to the selected Solar Orbiter mission profile, for the first time the poles of the Sun and the circumsolar region will be seen and studied from a privileged point of view near the Sun (minimum distance 0.28 AU). Metis features an innovative instrument design conceived for simultaneously imaging the visible (580-640 nm) and ultraviolet (Lyman α at 121.6 nm) emission of the solar corona. METIS is an externally occulted coronagraph which adopts an “inverted occulted” configuration. The inverted external occulter (IEO) is a circular aperture after which a spherical mirror M0 rejects back the solar disk light, which exits the instrument through the IEO aperture itself. The passing coronal light is then collected by the METIS telescope. Common to both channels, the Gregorian on-axis telescope is centrally occulted and both the primary and the secondary mirrors have annular shape. The optical and radiometric performance of the telescope is strongly dependent on the huge degree of vignetting presented by the optical design. The internal fields are highly vignetted by M0 and further vignetted by the internal elements, such as the internal occulter and the Lyot stop, furthermore the presence of some spiders, needed to mount the internal elements, are vignetting even more, in some parts of the FoV, the light beams. During the instrument commissioning, in the visible light channel some out-of-focus sources have been imaged while moving in the Metis FoV. At a first glance, the out-of-focus images exhibit a very strange pattern. The pattern can be explained by taking into account the peculiar design of the Metis coronagraph instrument; in fact, the not fully illuminated pupil gives rise to “half moon” shape out-of-focus images with the spiders casting their shadow in different positions. In this work, the ray-tracing simulation results for the out-of-focus images are compared with some of the images taken in flight; some considerations relating the shape and dimension of the acquired images with the distance from Metis of the sources are also given.
The EnVisS (Entire Visible Sky) instrument is one of the payloads of the European Space Agency Comet Interceptor mission. The aim of the mission is the study of a dynamically new comet, i.e. a comet that never travelled through the solar system, or an interstellar object, entering the inner solar system. As the mission three-spacecraft system passes through the comet coma, the EnVisS instrument maps the sky, as viewed from the interior of the comet tail, providing information on the dust properties and distribution. EnVisS is mounted on a spinning spacecraft and the full sky (i.e. 360°x180°) is entirely mapped thanks to a very wide field of view (180°x45°) optical design selected for the EnVisS camera. The paper presents the design of the EnVisS optical head. A fisheye optical layout has been selected because of the required wide field of view (180°x45°). This kind of layout has recently found several applications in Earth remote sensing (3MI instrument on MetOp SG) and in space exploration (SMEI instrument on Coriolis, MARCI on Mars reconnaissance orbiter). The EnVisS optical head provides a high resolved image to be coupled with a COTS detector featuring 2kx2k pixels with pitch 5.5µm. Chromatic aberration is corrected in the waveband 550-800nm, while the distortion has been controlled over the whole field of view to remain below 8% with respect to an Fθ mapping law. Since the camera will be switched on 24 hours before the comet closest encounter, the operative temperature will change during the approaching phase and crossing of the comet’s coma. In the paper, we discuss the solution adopted for reaching these challenging performances for a space-grade design, while at the same time respecting the demanding small allocated volume and mass for the optical and mechanical design. The view expressed herein can in no way be taken to reflect the official opinion of the European Space Agency.
EnVisS (Entire Visible Sky) is a space camera aboard the Comet Interceptor ESA mission. This is the first F-class space mission, a new generation of fast ESA missions, and it is scheduled for launch in 2029. Comet Interceptor aims to study, by means of in situ observations, a dynamically new comet, or interstellar object, that enters the Solar System for the first time. Approaching the comet, three modules will detach: spacecraft A will provide remote sensing and communications, while spacecraft B1 and B2 will cross the coma and fly-by the nucleus. EnVisS is a fish-eye camera with a field of view (FOV) of 180° × 45°. It is mounted on B2, which is spin stabilized; the spin provides the scanning motion for the camera allowing imaging the whole sky (180° × 360°) including the comet. The EnVisS optical head is composed of ten lenses; the collected visible light passes through a three-strip filter assembly before reaching the detector. The central filter strip is a broadband filter, while the sides filter strips are linear polarizers, with the aim of studying the polarization state of the light reflected by both the comet coma and its core. The optical performance of EnVisS has been evaluated through ray tracing analyses. In this paper, the ghost study will be described and ghost images will be shown. This analysis, performed in the ZEMAX OpticStudio®, highlights which optical element causes the most intense ghost images and shows their distribution over the detector.
Ariel (Atmospheric Remote-Sensing Infrared Exoplanet Large Survey) has been adopted as the M4 mission for ESA “Cosmic Vision” program. Launch is scheduled for 2029. ARIEL will study exoplanet atmospheres through transit spectroscopy with a 1 m class telescope optimized in the waveband between 1.95 and 7.8 μm and operating in cryogenic conditions in the temperature range 40-50 K. Aluminum alloy 6061, in the T651 temper, was chosen as baseline material for telescope mirror substrates and supporting structures, following a trade-off study. To improve mirrors reflectivity within the operating waveband and to protect the aluminum surface from oxidation, a protected silver coating with space heritage was selected and underwent a qualification campaign during Phase B1 of the mission, with the goal of demonstrating a sufficient level of technology maturity. The qualification campaign consisted of two phases: a first set of durability and environmental tests conducted on a first batch of coated aluminum samples, followed by a set of verification tests performed on a second batch of samples coated alongside a full-size demonstrator of Ariel telescope primary mirror. This study presents the results of the verification tests, consisting of environmental (humidity and temperature cycling) tests and chemical/mechanical (abrasion, adhesion, cleaning) tests performed on the samples, and abrasion tests performed on the demonstrator, by means of visual inspections and reflectivity measurements.
The performance of as-built optical instruments strongly depends on thermal and structural loads, since these boundary conditions can affect the geometry of optical surfaces. Variations of temperature influence the volume, and the shape, of the structure proportionally to the coefficient of thermal expansion of the material, while mechanical loads, like gravity, may induce deformations on the optical elements according to the set of applied constraints. Those effects can introduce aberrations that degrade the performance of the optical system. Since software for optical and thermo-structural analysis are usually different, a coupling methodology between these two fields of physics is needed. This is a step-by-step procedure through many platforms. In this work, the procedure devised and used by the authors will be presented. At first, a thermo-mechanical analysis (depending on the loads involved) has to be performed, in order to obtain the final deformed geometry of the optical structure; COMSOL Multiphysics is the finite element solver (FEM) used for these analyses. Then an output data file, containing the coordinates of points belonging to the optical surface, can be generated. The output data are elaborated by a MATLAB routine that allows to convert the set of points into an n-th polynomial expression that best fits the surface data. The fitted polynomial surface is hence imported in ZEMAX ray-tracing software to study the optical performances of the system and the effects of thermo-mechanical loads.
Entire Visible Sky (EnVisS) camera is one of the payload proposed for the ESA selected F-Class mission Comet Interceptor. The main aim of the mission is the study of a dynamic new comet, or an interstellar object, entering the inner solar system for the first time. The Comet Interceptor mission is conceived to be composed of three spacecraft: a parent spacecraft A and two, spacecraft B1 and B2, dedicated to a close and risky fly-by. EnVisS will be mounted on spacecraft B2, which is foreseen to be spin-stabilized. The EnVisS camera is designed to capture the entire sky in some visible wavelength bands while the spacecraft pass through the comet's coma. EnVisS optical head is composed of a fisheye lens with a field of view of 180° x 40° coupled with an imaging detector equipped with both band-pass and polarimetric filters. The design of fisheye lenses requires to take into account some issues typical of very wide-angle lenses. The fundamental origin of the optical problems resides on the entrance pupil shift at large angle, where the paraxial approximation is no more valid: chief rays angles on the object side are not preserved passing through the optics preceding the aperture stop (fore-optics). This effect produces an anamorphic deformation of the image on the focal plane, i.e. the focal length is changing along the elevation angles. Tracing the rays appropriately requires some effort by the designer. It has to be considered that distortion, including anamorphism, is an aberration that does not affect the quality of a point source image, thus it can be present also in well corrected lenses. In this paper the optical design of the mera for the ESA F-class "Comet Interceptor" mission, will be presented together with the initial optical requirements and the final expected optical performances.
EnVisS (Entire Visible Sky) is an all-sky camera specifically designed to fly on the space mission Comet Interceptor. This mission has been selected in June 2019 as the first European Space Agency (ESA) Fast mission, a modest size mission with fast implementation. Comet Interceptor aims to study a dynamically new comet, or interstellar object, and its launch is scheduled in 2029 as a companion to the ARIEL mission. The mission study phase, called Phase 0, has been completed in December 2019, and then the Phase A study had started. Phase A will last for about two years until mission adoption expected in June 2022. The Comet Interceptor mission is conceived to be composed of three spacecraft: spacecraft A devoted to remote sensing science, and the other two, spacecraft B1 and B2, dedicated to a fly-by with the comet. EnVisS will be mounted on spacecraft B2, which is foreseen to be spin-stabilized. The camera is developed with the scientific task to image, in push-frame mode, the full comet coma in different colors. A set of ad-hoc selected broadband filters and polarizers in the visible range will be used to study the full scale distribution of the coma gas and dust species. The camera configuration is a fish-eye lens system with a FoV of about 180°x45°. This paper will describe the preliminary EnVisS optical head design and analysis carried out during the Phase 0 study of the mission.
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