SpicA FAR infrared Instrument, SAFARI, is an imaging spectrometer which is being designed to map large areas of the sky in the far infrared. The SPICA mission, having a large cold telescope cooled to 6K above absolute zero, will provide an optimum environment where instruments are limited only by the cosmic background itself.
The next great leap forward in space-based far-infrared astronomy will be made by the Japanese-led SPICA mission, which is anticipated to be launched late 2020’s as the next large astrophysics mission of JAXA, in partnership with ESA and with key European contributions. Filling in the gap between JWST and ALMA, the SPICA mission will study the evolution of galaxies, stars and planetary systems. SPICA will utilize a deeply cooled 3m-class telescope, provided by European industry, to realize zodiacal background limited performance, high spatial resolution and large collecting area.
Making full advantage of the deeply cooled telescope (<6K), the SAFARI instrument on SPICA is a highly sensitive wide-field imaging photometer and spectrometer operating in the 34-210 μm wavelength range. Utilizing Nyquist-sampled focal-plane arrays of very sensitive Transition Edge Sensors (TES), SAFARI will offer a photometric imaging (R ≈ 2), and a low (R = 100) and medium resolution (R = 2000 at 100 μm) imaging spectroscopy mode in three photometric bands within a 2’x2’ instantaneous FoV by means of a cryogenic Mach-Zehnder Fourier Transform Spectrometer.
In this paper we will provide an overview of the SAFARI instrument design and system architecture. We will describe the reference design of the SAFARI focal- plane unit, the implementation of the various optical instrument functions designed around the central large-stroke FTS system, the photometric band definition and out-of-band filtering by quasioptical elements, the control of straylight, diffraction and thermal emission in the long-wavelength limit, and how we interface to the large-format FPA arrays at one end and the SPICA telescope assembly at the other end.
We will briefly discuss the key performance drivers with special emphasis on the optical techniques adopted to overcome issues related to very low background operation of SAFARI. A summary and discussion of the expected instrument performance and an overview of the astronomical capabilities finally conclude the paper.
SPICE is an imaging spectrometer operating at vacuum ultraviolet (VUV) wavelengths, 70.4 – 79.0 nm and 97.3 - 104.9 nm. It is a facility instrument on the Solar Orbiter mission, which carries 10 science instruments in all, to make observations of the Sun’s atmosphere and heliosphere, at close proximity to the Sun, i.e to 0.28 A.U. at perihelion. SPICE’s role is to make VUV measurements of plasma in the solar atmosphere. SPICE is designed to achieve spectral imaging at spectral resolution >1500, spatial resolution of several arcsec, and two-dimensional FOV of 11 x16arcmins. The many strong constraints on the instrument design imposed by the mission requirements prevent the imaging performance from exceeding those of previous instruments, but by being closer to the sun there is a gain in spatial resolution. The price which is paid is the harsher environment, particularly thermal. This leads to some novel features in the design, which needed to be proven by ground test programs. These include a dichroic solar-transmitting primary mirror to dump the solar heat, a high in-flight temperature (60deg.C) and gradients in the optics box, and a bespoke variable-line-spacing grating to minimise the number of reflective components used. The tests culminate in the systemlevel test of VUV imaging performance and pointing stability. We will describe how our dedicated facility with heritage from previous solar instruments, is used to make these tests, and show the results, firstly on the Engineering Model of the optics unit, and more recently on the Flight Model. For the keywords, select up to 8 key terms for a search on your manuscript's subject.
SpicA FAR infrared Instrument, SAFARI, is one of the instruments planned for the SPICA mission. The SPICA
mission is the next great leap forward in space-based far-infrared astronomy and will study the evolution of galaxies,
stars and planetary systems. SPICA will utilize a deeply cooled 2.5m-class telescope, provided by European industry, to
realize zodiacal background limited performance, and high spatial resolution. The instrument SAFARI is a cryogenic
grating-based point source spectrometer working in the wavelength domain 34 to 230 μm, providing spectral resolving
power from 300 to at least 2000.
The instrument shall provide low and high resolution spectroscopy in four spectral bands. Low Resolution mode is the
native instrument mode, while the high Resolution mode is achieved by means of a Martin-Pupplet interferometer.
The optical system is all-reflective and consists of three main modules; an input optics module, followed by the Band
and Mode Distributing Optics and the grating Modules. The instrument utilizes Nyquist sampled filled linear arrays of
very sensitive TES detectors.
The work presented in this paper describes the optical design architecture and design concept compatible with the
current instrument performance and volume design drivers.
This paper describes the optical design of the far infrared imaging spectrometer for the JAXA’s SPICA mission. The SAFARI instrument, is a cryogenic imaging Fourier transform spectrometer (iFTS), designed to perform backgroundlimited spectroscopic and photometric imaging in the band 34-210 μm. The all-reflective optical system is highly modular and consists of three main modules; input optics module, interferometer module (FTS) and camera bay optics. A special study has been dedicated to the spectroscopic performance of the instrument, in which the spectral response and interference of the instrument have been modeled, as the FTS mechanism scans over the total desired OPD range.
The Safari instrument on the Japanese SPICA mission is a zodiacal background limited imaging spectrometer offering a
photometric imaging (R ≈ 2), and a low (R = 100) and medium spectral resolution (R = 2000 at 100 μm) spectroscopy
mode in three photometric bands covering the 34-210 μm wavelength range. The instrument utilizes Nyquist sampled
filled arrays of very sensitive TES detectors providing a 2’x2’ instantaneous field of view. The all-reflective optical
system of Safari is highly modular and consists of an input optics module containing the entrance shutter, a calibration
source and a pair of filter wheels, followed by an interferometer and finally the camera bay optics accommodating the
focal-plane arrays. The optical design is largely driven and constrained by volume inviting for a compact three-dimensional
arrangement of the interferometer and camera bay optics without compromising the optical performance
requirements associated with a diffraction- and background-limited spectroscopic imaging instrument. Central to the
optics we present a flexible and compact non-polarizing Mach-Zehnder interferometer layout, with dual input and output
ports, employing a novel FTS scan mechanism based on magnetic bearings and a linear motor. In this paper we discuss
the conceptual design of the focal-plane optics and describe how we implement the optical instrument functions, define
the photometric bands, deal with straylight control, diffraction and thermal emission in the long-wavelength limit and
interface to the large-format FPA arrays at one end and the SPICA telescope assembly at the other end.
C. Miravet, D. Zorita, J. Bueno, L. Pascual, A. García Marín, G. Taubmann, J. Azcona, J. Arroyo, I. Monasterio, U. García, J. Martin, C. Mas, J. Muñoz, A. Lopez, J. Eguía, S. Jarabo, R. García, R. Navarro, T. Belenguer, L. González, C. Pastor, D. Arrazola, C. Gonzalez Alvarado, I. Cabeza, A. Borges, A. Marini, G. Crippa
Ingenio/SEOSAT is the flagship mission for the Spanish Space Plan 2007-2011, as is currently under development by a
Spanish industrial consortium in the framework of an ESA contract. Ingenio/SEOSAT is a multi-spectral high-resolution
optical satellite for Earth Remote Sensing, designed to provide imagery to different Spanish civil, institutional and
governmental users, and potentially to other European users in the frame of GMES and GEOSS. SEOSAT/Ingenio is a
Low Earth Orbiting mission. It features a Primary Payload (PP) with one 2.5 meter resolution panchromatic channel and
four 10 meter resolution visible/near infrared spectral channels. The PP swath close to 55 km ensures a frequent revisit
period, and offers quick accessibility to any point on Earth in emergency situations. In this paper are described the main
characteristics and development status of the instrument from an opto-mechancial point of view, as well as the estimated performance data.
IACATS is an atmospheric turbulence, stars and telescope simulator for the evaluation of on ground
telescopes instrumentation developed by INTA (optics) and LIDAX
(opto-mechanics) for the IAC (Instituto
de Astrofísica de Canarias).
Three telescopes have been simulated, matching the f number, focal plane, and optical interface of the
actual telescopes. An optical breadboard was designed and built containing the required opto-mechanics for
simulating the telescopes, and various levels of turbulence required.
In addition to the telescope simulator optics, a set of three phase plates have been procured and
conveniently combined in order to reproduce the atmospheric turbulence required by the IAC. A wave front
sensor has been also included in order to evaluate the deformation that the phase plates, or the simulated
turbulence, produce in the wave front coming from the illumination system and star simulator. Finally, a
specific illumination system was developed including different working wavelengths in order to fulfil the
requirements. The description of the illumination system itself has been done in a separate publication.. In the
following lines, the characteristics of the IACATS instrument as well as the results obtained from the AIV
(Assembly and Integration Verification) process are reported on.
The IACAT (IAC Atmosphere and Telescope) Simulator is an Optical Ground Support Equipment which simulates
atmospheric turbulence and reproduces the performance of three very different telescopes: GTC and WHT, located at
the Observatorio Del Roque de los Muchachos in La Palma (Canary Islands), and OGS which is located at the
Observatorio Del Teide in Tenerife (Canary Islands). Its mission is to provide Scientists with the same measurement
conditions as the real telescope but in a friendly laboratory environment, to assist in the development of new adaptive
optics methods based on FPGAs.
The most important telescope characteristics are simulated, such as f number, pupil size and position, magnification,
central obscuration, etc. Up to 13 stellar objects can be created, individually or as binary stars with specific angular
separations down to miliarcseconds.
For the atmosphere simulation, it allows the creation of three different turbulence layers concurrently with different
altitude and wind speed ranges.
Gonzalo Ramos Zapata, Tomás Belenguer Dávila, Carmen Pastor Santos, René Restrepo Gómez, Concepción González Alvarado, Hugo Laguna Hernández, Antonio Astolfi Carbonell, Javier Moreno Raso, Heribert Argelaguet, Javier Serrano
A LED based illumination system in which five Galilean collimation systems have been used is reported
on. It is part of a turbulence simulator for the evaluation of on ground telescopes instrumentation developed
by INTA (optics) and LIDAX (opto-mechanics) for the IAC called IACATS. The illumination requirements
(some visible and infrared lines) allow the use of five different LEDs (red, green, blue and two infrareds). In
order to optimize the illumination level of each wavelength, a Galilean collimating optical configuration was
constructed for each wavelength channel.
The IACATS instrument simulates a scene consisting of a set of different binary stars simulating the
required angular separation between them, ant their spectral characteristics. As a result, a visible and infrared
multi-spectral illumination system has been integrated as a part of the turbulence simulator, and the features
(opto-mechanical) and illumination characteristics are described in the following lines.
IMaX current status is reported on. IMaX, the Imaging Magnetograph eXperiment developed for a
Spanish consortium for the SUNRISE Mission, is a payload that will work simultaneously as a high
sensitivity polarimeter, a high resolving spectral power, and a near diffraction limited imager. Once every
mechanical element has been purchased, the assembly, integration, alignment and verification processes
(AIV process) has been carried out successfully. After a brief description of the IMaX opto-mechanical
elements that have been received, the integration sequence as well as the main results obtained during the
AIV process are presented.
Basically, AIV process consists on the opto-mechanical components assembly on the Optical Bench
(OB), the optical elements assembly on the previously integrated optomechanics, the alignment and
orientation of the opto-mechanical components, and the two-channels quality evaluation that allows to
leave the opto-mechanical components ready for the cameras integration and IMaX performance tests
characterization. Actually, the most relevant results related to the AIV process as well as the IMaX
performance firsts tests are presented.
In this work, it is described the Imaging Magnetograph eXperiment, IMaX, one of the three postfocal instruments of
the Sunrise mission. The Sunrise project consists on a stratospheric balloon with a 1 m aperture telescope, which will fly
from the Antarctica within the NASA Long Duration Balloon Program.
IMaX will provide vector magnetograms of the solar surface with a spatial resolution of 70 m. This data is relevant
for understanding how the magnetic fields emerge in the solar surface, how they couple the photospheric base with the
million degrees of temperature of the solar corona and which are the processes that are responsible of the generation of
such an immense temperatures.
To meet this goal IMaX should work as a high sensitivity polarimeter, high resolution spectrometer and a near
diffraction limited imager. Liquid Crystal Variable Retarders will be used as polarization modulators taking advantage of
the optical retardation induced by application of low electric fields and avoiding mechanical mechanisms. Therefore, the
interest of these devices for aerospace applications is envisaged. The spectral resolution required will be achieved by
using a LiNbO3 Fabry-Perot etalon in double pass configuration as spectral filter before the two CCDs detectors. As well
phase-diversity techniques will be implemented in order to improve the image quality.
Nowadays, IMaX project is in the detailed design phase before fabrication, integration, assembly and verification.
This paper briefly describes the current status of the instrument and the technical solutions developed to fulfil the
scientific requirements.
The Imaging MAgnetograph eXperiment, IMaX, is one of the three postfocal instruments of the Sunrise mission. The
Sunrise project consists of a stratospheric balloon with a 1 m aperture telescope, which will fly from the Antarctica
within the NASA Long Duration Balloon Program.
IMaX should work as a diffraction limited imager and it should be capable to carry out polarization measurements
and spectroscopic analysis with high resolution (50.000-100.000 range).
The spectral resolution required will be achieved by using a LiNbO3 (z-cut) Fabry-Perot etalon in double pass
configuration as spectral filter.
Up to our knowledge, few works in the literature describe the associated problems of using these devices in an
imager instrument (roughness, off-normal incidence, polarization sensitivity...). Because of that, an extensive and
detailed analysis of etalon has been carried out. Special attention has been taken in order to determine the wavefront
transmission error produced by the imperfections of a real etalon in double pass configuration working in collimated
beam. Different theoretical models, numeric simulations and experimental data are analysed and compared obtaining a
complete description of the etalon response.
Luis Colina, Eva Diaz, A. Aricha, M. Alcacera, A. Balado, Javier Barandiaran, D. Barrado y Navascues, Tomas Belenguer, J. Blanco, I. Figueroa, G. Garcia, L. Gonzalez, R.L. Heredero, F. Herrada, Carlos Laviada Hernandez, M. March, M. Menendez, C. Pastor, Manuel Reina, A. Sanchez
The MIRI Telescope Simulator (MTS) is part of the Optical Ground Support System (OGSE) for the verification and calibration phase of the James Webb Space Telescope (JWST) Mid-Infrared Instrument (MIRI). The MTS will simulate the optical characteristics of the JWST output beam in an environment similar to the flight conditions. The different functionalities of the MTS are briefly described and its current design, including the illumination and imaging subsystems, is presented.
The SUNRISE balloon project is a high-resolution mission to study solar magnetic fields able to resolve the critical scale of 100 km in the solar photosphere, or about one photon mean free path. The Imaging Magnetograph eXperiment (IMaX) is one of the three instruments that will fly in the balloon and will receive light from the 1m aperture telescope of the mission. IMaX should take advantage of the 15 days of uninterrupted solar observations and the exceptional resolution to help clarifying our understanding of the
small-scale magnetic concentrations that pervade the solar surface. For this, IMaX should act as a diffraction limited imager able to carry out spectroscopic analysis with resolutions in the 50.000-100.000 range and capable to perform polarization measurements. The solutions adopted by the project to achieve all these three demanding goals are explained in this article. They include the use of Liquid Crystal Variable Retarders for the polarization modulation, one
LiNbO3 etalon in double pass and two modern CCD detectors that allow for the application of phase diversity techniques by slightly changing the focus of one of the CCDs.
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