The Ariel space mission will characterize spectroscopically the atmospheres of a large and diverse sample of hundreds of exoplanets. Through the study of targets with a wide range of planetary parameters (mass, density, equilibrium temperature) and host star types the origin for the diversity observed in known exoplanets will be better understood. Ariel is an ESA Medium class science mission (M4) with a spacecraft bus developed by industry under contract to ESA, and a Payload provided by a consortium of national funding agencies in ESA member states, plus contributions from NASA, the CSA and JAXA. The payload is based on a 1-meter class telescope operated at below 60K, built all in Aluminium, which feeds two science instruments. A multi-channel photometer and low-resolution spectrometer instrument (the FGS, Fine Guidance System instrument) operating from 0.5 – 1.95 microns in wavelength provides both guidance information for stabilizing the spacecraft pointing as well as vital scientific information from spectroscopy in the near-infrared and photometry in the visible channels. The Ariel InfraRed Spectrometer (AIRS) instrument provides medium resolution spectroscopy from 1.95 – 7.8 microns wavelength coverage over two instrument channels. Supporting subsystems provide the necessary mechanical, thermal and electronics support to the cryogenic payload. This paper presents the overall picture of the payload for the Ariel mission. The payload tightly integrates the design and analysis of the various payload elements (including for example the integrated STOP analysis of the Telescope and Common Optics) in order to allow the exacting photometric stability requirements for the mission to be met. The Ariel payload has passed through the Preliminary Design Review (completed in Q2 2023) and is now developing and building prototype models of the Telescope, Instruments and Subsystems (details of which will be provided in other contributions to this conference). This paper will present the current status of the development work and outline the future plans to complete the build and verification of the integrated payload.
We report on the design of 2ES (Second Earth Initiative Spectrograph): a new fiber-fed, high-resolution, high-precision radial velocity echelle spectrograph for the 2.2m ESO/MPG telescope in Chile, which will cover the visible wavelength range ∼370nm to 850nm with a resolution of 120, 000. 2ES will be dedicated to a >5-year observing program with access to the majority (2/3) of the telescope time with the goal of discovering temperate terrestrial Earth-mass planets in the habitable zone around the bright solar-type stars. To achieve this goal, 2ES aims for ultra-high instrumental radial-velocity precision and an observing strategy that involves high-cadence observation of the brightest Sun-like stars in the Southern Hemisphere. Here, we present an overview of the project, its observation strategy, the optical design as well as the opto-mechanical concepts and calibration strategies to achieve the required instrument stability.
The NISP (Near Infrared Spectrometer and Photometer) is one of the two Euclid instruments (see ref [1]). It operates in the near-IR spectral region (950-2020nm) as a photometer and spectrometer. The instrument is composed of: - a cold (135K) optomechanical subsystem consisting of a Silicon carbide structure, an optical assembly, a filter wheel mechanism, a grism wheel mechanism, a calibration unit and a thermal control system - a detection system based on a mosaic of 16 H2RG with their front-end readout electronic. - a warm electronic system (290K) composed of a data processing / detector control unit and of an instrument control unit that interfaces with the spacecraft via a 1553 bus for command and control and via Spacewire links for science data This paper presents: - the final architecture of the flight model instrument and subsystems - the performances and the ground calibration measurement done at NISP level and at Euclid Payload Module level at operational cold temperature.
The Atmospheric Remote-Sensing Infrared Exoplanet Large-survey, ARIEL, has been selected to be the next (M4) medium class space mission in the ESA Cosmic Vision programme. From launch in 2028, and during the following 4 years of operation, ARIEL will perform precise spectroscopy of the atmospheres of ~1000 known transiting exoplanets using its metre-class telescope. A three-band photometer and three spectrometers cover the 0.5 µm to 7.8 µm region of the electromagnetic spectrum.
This paper gives an overview of the mission payload, including the telescope assembly, the FGS (Fine Guidance System) - which provides both pointing information to the spacecraft and scientific photometry and low-resolution spectrometer data, the ARIEL InfraRed Spectrometer (AIRS), and other payload infrastructure such as the warm electronics, structures and cryogenic cooling systems.
The Euclid mission objective is to understand why the expansion of the Universe is accelerating through by mapping the geometry of the dark Universe
by investigating the distance-redshift relationship and tracing the evolution of cosmic structures. The Euclid project is part of ESA's Cosmic Vision
program with its launch planned for 2020 (ref [1]).
The NISP (Near Infrared Spectrometer and Photometer) is one of the two Euclid instruments and is operating in the near-IR spectral region (900-
2000nm) as a photometer and spectrometer. The instrument is composed of:
- a cold (135K) optomechanical subsystem consisting of a Silicon carbide structure, an optical assembly (corrector and camera lens), a filter wheel
mechanism, a grism wheel mechanism, a calibration unit and a thermal control system
- a detection subsystem based on a mosaic of 16 HAWAII2RG cooled to 95K with their front-end readout electronic cooled to 140K, integrated on a
mechanical focal plane structure made with molybdenum and aluminum. The detection subsystem is mounted on the optomechanical subsystem
structure
- a warm electronic subsystem (280K) composed of a data processing / detector control unit and of an instrument control unit that interfaces with the
spacecraft via a 1553 bus for command and control and via Spacewire links for science data
This presentation describes the architecture of the instrument at the end of the phase C (Detailed Design Review), the expected performance, the
technological key challenges and preliminary test results obtained for different NISP subsystem breadboards and for the NISP Structural and Thermal
model (STM).
The ESA mission Euclid is designed to explore the dark side of the Universe. The NISP (Near Infrared Spectro-
Photometer) is one of its two instruments operating in the near-IR spectral region (0.9-2μm), that will be fully integrated
and tested at Laboratory d’Astrophysique de Marseille (LAM) under vacuum and thermal conditions. The test campaign
will regroup functional tests, performance tests, calibration procedure validation and observations scenario test. One of
the main objectives of the test campaign will be the measurement of the focus position of NISP with respect to the
EUCLID object plane. To achieve these tests campaign, a global Ground Support Equipment (GSE) called the
Verification Ground System (VGS) has to be developed. It will be a complex set of GSE integrated in ERIOS chamber
made of: a telescope simulator to simulate the EUCLID telescope and to inject light into NISP, a thermal environment to
be used for NISP thermal balance and verification, a sets of mechanical interfaces to align all the parts into ERIOS
chamber, the NISP Electrical GSE (EGSE) to control the instrument during the test and a metrology system to measure
the positions of the components during the test. We will present the preliminary design and concepts of the VGS and we
will show the main difficulties we have to deal with: design of thermal environment at 80K with 4mK stability, the
development of a metrology system in vacuum, knowledge of the focus position within 150μm in cold, etc. The main
objectives of the NISP test will be explained and how the VGS responds to the test requirement.
X-shooter is a second generation VLT instrument currently under construction by a Consortium of Institutes from Denmark, Italy, The Netherlands, France and ESO. X-shooter is designed to acquire intermediate (5000-10000) resolution spectra of single objects in an unprecedented wide wavelength coverage (320-2500 nm). In order to maximize efficiency the beam is divided into 3 arms (UV, VIS and NIR) by a system of dichroics. X-shooter is designed for the Cassegrain focus of one VLT unit. The mechanical assembly has to provide specific solutions to maintain 3 arms within the strict tolerances required by the intermediate resolution, during the typical motions of the Cassegrain focal station. It must as well ensure the permanent co-alignment of the 3 slits and the stability of the spectral format on the focal plane of each arm, allowing long intervals between calibration exposures. The above requirements have been met via an innovative mechanical design merging passive stiffness and active control to obtain a light, accessible and functional assembly. This paper gives a description of the X-shooter mechanical assembly with main emphasis on the common "backbone" structure and the UV- and VIS spectrograph arms.
Traditionally, instruments for astronomical telescopes are built in Aluminium plate structures, but with the increasing demand for complexity and consequent increase in mass (e.g. the instruments for Very Large Telescopes (VLT) and the future eXtremely Large Telescopes (XLT)), lightweight structures of Carbon Fibre Reinforced Plastic (CFRP) become attractive. CFRP-structures give higher stiffness per unit weight and are less sensible to temperature variations. As an example the performance of a CFRP lattice structure for the ESO VLT X-shooter instrument is compared with the present design of the Aluminium.
The design of the Primary Structure of the Mid Infra-Red Instrument (MIRI) onboard the NASA/ESA James Webb Space Telescope will be presented. The main design driver is the energy flow from the 35 K "hot" satellite interface to the 7 K "cold" MIRI interface. Carbon fibre reinforced plastic (CFRP) was chosen for this application due to the low thermal conductivity at cryogenic temperatures, high strength and low density. Details of the qualification program will be given.
When applying noxious heat stimuli to human skin in the study of the pain system, one of the main problems is not to cause permanent damage. A better understanding of the temperature distribution and the propagation of heat, i.e. heat flux, in human skin is thus needed. In order to investigate these problems thoroughly, we have developed a 3-dimensional finite element model (FEM) 4-layer of human skin. The model is kept simple for better understanding of the boundary problems. The water content in each layer is used for determining the thermal properties. It is therefore not a homogenous structure. In this model the stratum corneum has been included with lower water content than in the epidermis. Simulations shows that the surface temperature reaches high levels whereas the temperature in the deeper structure is much lower. Thermal and optical constants found in the literature was applied. Heat propagation downwards and outwards from the source has been investigated to understand of the accumulation of energy in the boundary between two layers. Prediction of the heat flux at boundary between the epidermis and dermis shows that for repetitive stimulation there is a risk of exceeding the threshold temperature of 65 degrees Celsius for irreversible damage.
A 25 m four mirror live optics telescope is studied. M1 is spherical with 141 segments and f/0.96. M1 is re-imaged onto M4, also with 141 segments. Image FWHM is less than 0.10 arc sec over greater than 20 arc min. A horseshoe solution with a simple azimuth platform is applied. M1 segments are supported by a fine meniscus form truss structure, tied to the horseshoes by a coarser mesh. A FEM with 104 dof was developed and applied. Live optics control M1 and M4 segments (the latter with potentially high bandwidth), M1/M4 segment balancing and servos. Correction signals in tilt, coma and defocus are traced. A correlation tracker and a laser guide star system are included. Low and high wind speed regimes are studied. An end-to-end simulation model is developed, based on modal representation of our FEM. Image quality dependence on wind load is studied from segment piston and tilt deflections. Eigenmodes are recorded. Using wind time series, we study dynamic effects and image quality resulting from the 141 segment spots. Automatic segment control at a bandwidth of only 1 Hz gives excellent image quality. We foresee to reach a bandwidth greater than 50 Hz, securing a system partly adaptive, with effects of atmospheric wave front tilt removed through M4 segment tilting at high frequency. Further progress include optimization of mechanical design and end-to-end simulation model, wind tunnel testing and studies of wave front sensor, correlation tracker and instruments. A fully adaptive system is tentatively studied as is coherent operation at IR wavelengths.
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