In 2019, the FORUM mission (Far-infrared Outgoing Radiation Understanding and Monitoring) has been selected by ESA as Earth Explorer 9 mission. FORUM aims to record the emission spectrum of the Earth’s stratosphere and troposphere in the spectral range of 100 to 1600 cm-1 (i.e. 6.25μm to 100 μm). It will measure the spectral features of the far-infrared contribution to the Earth radiation budget with the focus on the water vapour contribution, the cirrus cloud properties, and the ice/snow surface emissivity. FORUM’s primary optical instrument is a non-imaging Fourier Transform Spectrometer (FTS) scanning the Earth atmosphere in a step-and-stare acquisition mode sounding a 15 km ground sampling with a ground sampling distance of 100 km. A consortium led by TAS-UK as mission and platform prime and OHB as instrument prime are currently developing the satellite and payload together with Leonardo Italy and MICOS during an ESA phase A / B1 study. This consortium is one of the 2 independent consortia selected for FORUM’s phase A/B1. The paper will describe the design concept of the FORUM FTS instrument with main focus on the optical design. The key optical subsystems are the pointing unit and a double pendulum interferometer with an entrance three-mirror-anastigmatic telescope. The prediction of the performance with respect to threshold and goal requirements will be presented. Furthermore, the status of the beam splitter pre-development will be reported, in particular the development of an optical element based on a CVD-diamond substrate and a technology to manufacture broad band anti-reflective microstructures on a diamond surface. The microstructures are designed to suppress parasitic reflections in the spectral range between 6.25μm and 100μm. The highest efficiency occurs between 13 and 30μm, where the Fresnel reflection is reduced from 17% down to below 3.5%.
Significant progress has been made over the past years in the understanding of Earth’s climate; however, there are still uncertainties in the modelling of atmospheric radiative processes. The main radiative processes relevant for climatological models are related to atmospheric water vapour, clouds, and surface emissivity across the full thermal infrared spectrum. Whilst the mid-infrared outgoing radiation is currently measured from space (e.g. IASI), there is a lack of spectrally resolved measurements over a significant portion of Earth’s thermal emission in the Far-InfraRed (FIR) i.e. between 100 and 667 cm-1 (15-100 micron). FORUM (Far-infrared Outgoing Radiation Understanding and Monitoring) has been selected as the ESA’s ninth Earth Explorer mission in September 2019. FORUM aims at measuring the Earth’s Top-Of-Atmosphere emission spectrum from 100 to 1600 cm-¹ (i.e. 6.25 to 100 μm). Two independent instrument concepts, based on a Fourier Transform Spectrometer, have been thoroughly studied in Phase A preparatory activities, including the development of a breadboard of the interferometer. In addition, critical technologies have been identified and subjected to comprehensive breadboard studies in order to mitigate development risks and to raise the Technology Readiness Level (TRL). This has led to the development and characterisation of several beamsplitter candidates, the measurement of the emissivity of the black coating for the on-board blackbody, the verification of noise and responsivity performance of pyroelectric detectors and the characterisation of the interferometer mechanism.
Atmospheric monitoring missions aim at products like O3, H2O, NO2, SO2, BrO, CH4, CO, CO2 as well as aerosols and cloud information. Depending on the application area (Ozone Monitoring, Green House Gas Monitoring, Tropospheric Composition and Air Quality, Chemistry Climate Interaction etc.) total or tropospheric columns as well as profile information is required. The user community of these data as well as their central requirements w.r.t. the payload aspects will be described. A large range of relevant passive instrument types is available, in particular imaging spectrometer, sounder and polarisation measuring systems in the UV-VIS, SWIR and TIR spectral range. Differences between instruments for dedicated missions are highlighted and evolution of requirements is explained, also in comparison with relevant existing instrumentation partly in orbit today. Aspects of technology roadmaps for instrument implementation as well as synergetic effects of instrument combinations and according mission scopes are discussed.
The feasibility of a compact Fourier-Transform-Imaging-Spectrometer (FTIS) for small satellite remote sensing missions is currently being studied under ESA contract. Compared to classical hyperspectral imagers using dispersive spectrometers the major advantages of the FTIS is the compact optics module and the tolerable higher detector temperature, thus easing the instrument thermal design. The feasibility of this instrument concept will be demonstrated by breadboarding.
The near-infrared spectrograph (NIRSpec) is part of the James Webb Space Telescope (JWST) science mission: NIRSpec is a spectrograph that works in the near infrared spectral region (0.6micron - 5.0micron) and allows the observation of spectral features of the incident star light with different spectral resolution (R=100, R=1000, R=3000). It is designed for spectroscopy of more than 100 objects simultaneously. The optical design of the NIRSpec instrument is characterized by a straight optical system layout: It constitutes of a set of optical modules of similar optical design type with high performance and low module tolerances.
The NIRSpec instrument development is a cooperation of the European Space Agency and EADS Astrium Germany GmbH as prime contractor for instrument development, design, and manufacturing.
The NIRSpec instrument on the James Webb Space Telescope (JWST) is a multi-object spectrograph capable of measuring the near infrared spectrum of at least 100 objects simultaneously at various spectral resolutions. It operates under cryogenic conditions (T~ 35 K). NIRSpec is part of the JWST science instruments suite. Its main purpose is to provide low (R=100), medium (R=1000) and high resolution (R=2700) spectroscopic observations over the wavelength range 0.6 μm - 5.0 μm in support of the four JWST science programs. The NIRSpec instrument is being developed by the European Space Agency with EADS Astrium Germany GmbH as the prime contractor.
The James Webb Space Telescope (JWST) is a passively cooled, 6.5m aperture class telescope, optimized for diffraction-limited performance in the near-infrared wavelength region (1 - 5 μm). JWST will be capable of high-resolution imaging and spectroscopy and will carry a scientific payload consisting of three scientific instruments. One of the instruments - NIRSpec - is a near-infrared, multi-object, dispersive spectrograph, which will be provided by ESA.
EADS Astrium and its subcontractors have been involved in all ESA instrument studies for JWST. The actual NIRSpec design has evolved during three years of studying of different spectrometer design and performance options. Basic feature of the current design is the all ceramic material concept for the instrument structure and mirror optics; both were successfully tested on component level. This paper presents our NIRSpec design concept and its predicted performance.
KEYWORDS: Mirrors, James Webb Space Telescope, Actuators, Prototyping, Optical filters, Space telescopes, Spectrographs, Linear filtering, Sensors, Astronomical imaging
In 2011 NASA and ESA plan to launch the James Webb Space Telescope (JWST) as dignified successor of the Hubble Space Telescope. Three scientific instruments will cover the wavelength regions in the near-infrared (0.6-5μm, NIRCam and NIRSpec) and in the mid-infrared (5-28μm, MIRI), respectively. The ESA-led multi-object spectrograph NIRSpec as major European contribution is presently entering the detailed design phase in a collaboration between European space industries, scientific institutes, ESA and NASA. To allow for various operational modes in the instrument’s optical train several cryo-mechanisms are required, i.e. wheels for exchanging optical elements like filters and gratings as well as linear actuators on refocusing mirrors. We will give an overview on the detailed design, the prototyping and the testing of those mechanisms comprising highest reliability in the cryo-vacuum (~ 35K) combined with minimal power dissipation (~ 5mW on average), ultimate position accuracy (~ 0.5 - 1arcsec) combined with high launch vibration capability (ARIANE 5, ~ 60g) and a very long lifetime (~ 15 years) for ground tests and space operation under various environmental conditions. To reach this goal in a low cost and risk approach we rely on the heritage from ESA's earlier infrared missions, i.e. ISO and HERSCHEL.
KEYWORDS: Mirrors, James Webb Space Telescope, Actuators, Picture Archiving and Communication System, Optical components, Optical filters, Calibration, Electronics, Prisms, Spectrographs
The Mid-Infrared Instrument (MIRI) and the Near-Infrared Spectrograph (NIRSpec) of the JWST require various mechanisms for positioning optical elements in cryo-vacuum environment (7K resp. 35K): Wheels for exchanging filters, gratings and prisms, a flip mirror for switching between the sky and internal calibration sources and a linear actuator for refocusing purposes will have to be developed. In order to fulfill the stringent requirements of the mission, comprising to survive a warm ARIANE 5 launch, to guarantee high accuracy positioning in the cryovacuum with minimal power dissipation, to be operational with high reliability during 10 years of lifetime and to be testable under various environmental conditions, we propose a low cost and low schedule risk approach, based on the successful flight experience and qualification heritage from ESA’s infrared missions ISO and HERSCHEL.
An imaging FTS would be capable of carrying out many of the programs in the DRM, namely all those which require imaging and/or low spectral resolution wide field/multi-object spectroscopy. We review the DRM science areas, describing the relevance of an imaging FTS. Required instrumental capabilities are then derived from the science goals. Our compact camera and imaging FTS instrument design emphasizes simplicity with a single optical train covering a field 6 X 3 arcmin2, with a fixed spatial sampling of 0.03 arcsec/pixel on a 12 k X 6 k detector array.
An Integral Field and Multiobject Spectrograph (IFMOS) for NGST has been studied for the European Space Agency by a European consortium. This paper describes the design of the integral field unit (IFU), the optical system which divides up the 2D field and reformats in into one or more slits. The IFU uses the Advanced Image Slicer concept, which has many advantages over other designs of IFU and is particularly well suited to space applications.
A near and a mid infrared imaging camera for the NGST are presented, which were studied under ESA contract. Imaging in the 1 to 5 microns domain, possibly extended to 0.6 microns is a strong requirement for the core programs identified for NGST. Our compact near-IR camera design emphasizes simplicity with a single optical train covering a field 6 X 3 arcmin2 with a fixed spatial sampling of 0.03 arcsec/pixel on a 12 k X 6 k detector array. Three filter wheels allow for broad band and narrow band imaging. A mid- IR camera on NGST will be capable of carrying out aspects of many programs in the DRM. In addition to mid-IR is relatively unexplored at the spatial resolution and sensitivity NGST will be capable of, and so there is great potential for serendipitous science. A compact mid-IR camera design is presented covering a field 2.5 X 2.5 arcmin2 in the spectral range from 5 - 28 micrometers with two optical channels and a critical spatial sampling of 0.075 arcsec at 5 micrometers and 0.15 arcsec at 10 micrometers wavelengths.
We present the design of a mid-IR (5 - 28 micrometers ) integral field spectrometer for NGST. Details of the opto-mechanical design are given with particular attention being paid to those aspects influenced by the cryogenic, low background space environment in which the instrument needs to work. The instrument consists of three subsections: fore-optics and image slicing integral field units (IFU's), a 5 - 10 micrometers spectrograph and 10 - 28 micrometers spectrograph. Two co-aligned fields of view are separated into two wavelength channels (5 - 10 and 10 - 28 micrometers ) by a dichroic mirror in the fore- optics which also re-image the telescope focal plane onto the slicing mirrors of two IFU's.
Bernd Harnisch, Marino Fabbricotti, Roland Meynart, Bernd Kunkel, Winfried Posselt, Elke Schmidt, Robert Davancens, Olivier Donnadieu, Olivier Saint-Pe, Dave Charlton, Liz Sankus, Giuseppe Basile, L. Calamei, Juergen Schweizer, Hans Juranek, Rolf Sand, Horst Schwarzer, Karl-Heinz Suemnich, Philip Slater
The recent developments within the ESA funded HRIS (high resolution imaging spectrometer) technology program -- aiming at an airborne demonstrator model -- yielded rather successful subsystem developments. HRIS is designed as a true pushbroom hyperspectral imager with comparatively high spatial and spectral resolution, covering the spectral range from 450 to 2350 nm. The main breadboard units, with a space-near design, are essentially: a TMA (three mirro anastigmat, Carl Zeiss) front optics, a dual path spectrometer optics (Officine Galileo) with a novel in-field spectral separation unit, a 2-D SWIR CMT detector array with a dedicated CMOS readout multiplexer (GEC Marconi IR, MATRA MSF for testing), the signal processing electronics (DSS), some calibration elements (DLR + DSS), and the extensive testing of all units. The paper presents the essential results per unit, with possible exception of the front optics (which may not be completed at the conference paper presentation yet), including derived further development efforts. Also, the remaining steps towards an airborne test mission are outlined, together with a brief description of the envisaged high-altitude aircraft. We hope that this paper may also stir some potential users of later airborne HRIS test missions over dedicated target areas. Positive responses would support ESA to pursue the program. The technology units development under the HRIS contract have turned out useful for follow-on instrument developments such as the ESA Explorer mission candidate PRISM (processes research by an imaging space mission). This leads to the conclusion that the achieved development results are a sound basis for future airborne and spaceborne hyperspectral imager developments in Europe. A brief survey of the current PRISM baseline concept is added to the paper.
The recent developments of airborne imaging spectrometers, currently mostly designated hyperspectral imagers, in the spectral regime from 400-2400 nm revealed and proved an enormous application potential for remote sensing of vegetation in particular. Current spaceborne instrument developments and soon mission will expand these applications to regional and global scale surveys and monitoring. Hyperspectral imagers covering the a.m. spectral range promise to represent the ideal future remote sensing tool for vegetation type and status monitoring. The paper starts with a compilation of relevant applications - with emphasis on vegetation and soils - and their particular spectral and radiometric requirements which has been established by the main author recently as part of a Dornier Satellitensysteme (DSS) in-house activity, including a survey of existing and planned instruments of this type. To the possible extent, airborne measurement data from existing instruments will be included to underline the application potential. The second part will provide an insight into current development activities at DSS, mainly as results of ESA contracts, covering instruments such as ROSIS, HRIS demo model and current PRISM studies. The two latter instruments are ideally suited for vegetation monitoring in terms of pixel size, spectral resolution and range from 450-2350 nm, and radiometric performance. An outlook will conclude the paper for future developments and planning for operational hyperspectral missions.
PRISM is a future spaceborne hyperspectral imager, to operate in the spectral range from 450 nm to 12.3 micrometers . The PRISM instrument designer faces a challenging requirement - the absolute radiometric accuracy of the instrument in the range from 450 nm to 2350 nm shall be better than 2 percent of the measured radiance. This requirement can only be met using highly accurate characterization sources and a thermally stable instrument. In the DSS PRISM concept a calibration module is located separate from the optical module on an adjacent platform panel. The characterization sources are accessed via a pointing mirror, which is protruding over the platform edge. THis configuration allows for a wide across track coverage and access to the three on- board characterization units and to cold space. The three on-board characterization units are an aperture plate with small hole apertures for direct sun viewing, a reflective diffuser and a blackbody with selectable heater levels. Laser sources illuminating the diffuser serve as spectral references. The high accuracy in the VNIR/SWIR range is achieved by subsequent characterization measurements using the aperture plate and the diffuser: the first serves as absolute radiation reference for a limited amount of pixels, whereas the later will provide uniform illumination of all pixels and thus allows to correlate the sensitivities of the absolutely measured pixels to the others.
PRISM is a spaceborne hyperspectral imager for a future land surface research mission, whose prime objective is the observation of biophysical processes at a local to regional scale. PRISM is designed for a dedicated medium-size satellite in a polar sun-synchronous 11:00 h orbit, and will provide coregistered spectral images in tow spectral regions: from the visible to short-wave IR range with a spectral resolution of about 10 nm and two bands in the thermal IR from 10.3 micrometers to 12.3 micrometers . The presented instrument concept comprises four modules with separate interfaces to the platform: the optical, calibration, cooler and electronics modules. The optics module design is based on a pushbroom type of imaging spectrometer in which the entire field of view is imaged on four detector arrays. The long-wavelength arrays are cooled by tow pairs of Stirling cycle coolers. The instrument layout and platform accommodation are optimized to meet the high radiometric accuracy requirement. The key element of the instrument is the pointing unit, whose mirror is protruding over the platform edge for a wide across track coverage and or access to the three on-board characterization units and to cold space. The pointing unit will provide global accessibility in 3 days. A platform rotation in pitch will enable BRDF measurements of ground test sites by varying along track pointing angles.
The PRISM instrument is an imaging radiometer to be flown on a satellite in Earth orbit. The principle mission is to gather Earth radiance data from land areas, at a spatial resolution of approximately 50 m. It will have spectral resolution in the order of 10 nm in the visible to short- wave IR spectral band, and a few discrete spectral bands in the thermal IR. It will typically be operated to record multi-spectral images of selected areas about 50 km square. The field of view of the instrument must be capable of pointing control, in both across-track and along-track directions, to select specific targets in each orbit and to view selected targets in different directions. The instrument is in an early stage of concept development, in competitive studies carried out for the European Space Agency. The paper describes the principle conclusions of the initial study of the team led by Dornier Satellite Systems, with Sira and Matra Marconi Space as principle sub- contractors. Outline designs are presented for: pointing optics, imaging and relay optics, imaging spectrometer, channel separation and in-flight characterization. Brief notes are given on design trade-offs and rationales for baseline selections.
Dasa (Daimler-Benz Aerospace) currently is in charge of an ESA contract for the PRISM feasibility study, including MATRA MS/France and SIRA/UK. The main PRISM mission objectives are to monitor selected target areas with emphasis on bio-chemical stress analyses which are the subject of changes such as vegetation, in particular deforestation; further areas include glaciers, land/water boundaries, and similar features. The Dasa study team makes use of a similar ESA instrument currently the subject of dedicated subunits technology developments, the HRIS (high resolution imaging spectrometer), also lead by Dasa. Its main features and technology developments are covered in a survey. PRISM is covering most of the HRIS features, i.e., it will have an imaging spectrometer segment for the visible/NIR and the SWIR spectrum (450-2350 nm) as HRIS, but implements four MIR and TIR channels to provide surface temperature data, represented by linear detector arrays (essentially the features of another currently pursued ESA development program designated HRTIR). In a first study phase it also included a novel feature, a wide-angle two-axis pointing system for along- and across-track pointing in order to yield multi-directional reflectance data of dedicated targets, which turned out to be the greatest design driver in the instrument, it was omitted in the later phases. The geometric sampling interval is defined to 50 m (design goal) at 50 km swath. PRISM is currently studied in a feasibility study in a competitive way by two teams, one being lead by Dasa. At the time of the Symposium both studies are completed. The results of the Dasa team are presented. Since PRISM covers most of the HRIS mission it is rather likely that in the case of a successful concept feasibility proof (performance and technology wise), it may later replace the HRIS instrument. It is anticipated that a major part of the technology developments currently performed for HRIS will be utilized -- with some modifications -- for PRISM as well.
MIPAS is a high-resolution limb sounding Fourier spectrometer, designed to measure atmospheric trace gases in the medium and thermal infrared from the upper troposphere to the thermosphere. The main scientific objective of MIPAS is to obtain more precise data on the composition, dynamics, and radiation from the tropopause to the mesosphere. Specific measurement goals of the MIPAS experiment are the ozone chemistry and monitoring of the major greenhouse gases on a global scale, as well as the investigation of dynamic transport phenomena and the middle atmosphere radiation field. MIPAS has been conceived in harmonized feasibility and definition studies for two programs: the European Space Agency's Earth Observation Preparatory Program for the first Polar Orbiting Earth Observation Mission (POEM-1) and the German environmental research satellite program ATMOS.
Access to the requested content is limited to institutions that have purchased or subscribe to SPIE eBooks.
You are receiving this notice because your organization may not have SPIE eBooks access.*
*Shibboleth/Open Athens users─please
sign in
to access your institution's subscriptions.
To obtain this item, you may purchase the complete book in print or electronic format on
SPIE.org.
INSTITUTIONAL Select your institution to access the SPIE Digital Library.
PERSONAL Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.