The Mid-Infrared Instrument (MIRI) of the James Webb Space Telescope, scheduled for launch in 2013, will provide a
variety of observing modes such as broad/narrow-band imaging, coronagraphy and low/medium resolution
spectroscopy. One filter wheel and two dichroic-grating wheel mechanisms allow to configure the instrument between
the different observing modes and wavelength ranges. The main requirements for the three mechanisms with up to 18
positions on the wheel include: (1) reliable operation at T ~ 7 K, (2) optical precision, (3) low power dissipation, (4)
high vibration capability, (5) functionality at 6 K < T < 300 K and (6) long lifetime (5-10 years). To meet these stringent
requirement, a space-proven mechanism design based on the European ISO mission and consisting of a central bearing
carrying the optical wheels, a central torque motor for wheel actuation, a ratchet system for precise and powerless
positioning and a magnetoresistive position sensor has been selected. We present here the detailed design of the flight
models and report results from the extensive component qualification.
KEYWORDS: Current controlled current source, James Webb Space Telescope, Actuators, Contamination control, Mid-IR, Coronagraphy, Temperature metrology, Shape memory alloys, Fermium, Frequency modulation
During its cold mission phase at 7 Κ the Mid Infrared Instrument (MIRI) is the coldest spot on the James
Webb Space Telescope (JWST) and will act consequently as a cryopump of the instrument's environment. Since
the absorption of outgassing molecules from the spacecraft (mainly water and hydrocarbons) on optical surfaces
would lead to a significant degradation of the optical performance of MIRI, a Contamination Control Cover
(CCC) has been introduced. This cover is placed in the entrance optical path of MIRI right after the picko.
mirror (POM) and will be closed during the instrument's cool down phase and at MIRI's operational temperature
each time the POM is heated up for decontamination. The CCC will be used further as an optical shutter for
dark sky calibration and for the protection against latency images which might emerge from coronagraphic filter
changes. Therefore, the CCC has been designed to be multi operational with approximately 3000 life cycles. A
contact-free labyrinth seal allows the required reduction of molecular flow towards the instrument and avoids the
possibility of any freezing. The CCC is operational between 300 Κ and 7 Κ and is actuated by two redundant
stepper motors. In this paper we describe the design of the CCC and the results of the qualification campaign.
Further a dedicated measurement of its molecular conductance at various temperatures is presented.
MIRI is the mid-IR instrument for the James Webb Space Telescope and provides imaging, coronography and integral
field spectroscopy over the 5-28μm wavelength range. MIRI is the only instrument which is cooled to 7K by a dedicated
cooler, much lower than the passively cooled 40K of the rest of JWST, which introduces unique challenges. The paper
will describe the key features of the overall instrument design. The flight model design of the MIRI Optical System is
completed, with hardware now in manufacture across Europe and the USA, while the MIRI Cooler System is at PDR
level development. A brief description of how the different development stages of the optical and cooling systems are
accommodated is provided, but the paper largely describes progress with the MIRI Optical System. We report the
current status of the development and provide an overview of the results from the qualification and test programme.
W. Hajdas, N. Produit, E. Suarez-Garcia, F. Barao, C. Casella, K. Deiters, S. Deluit, C. Leluc, A. Mchedlishvilli, M. Pohl, D. Rapin, Ch. Tao, J.-P. Vialle, R. Walter, C. Wigger, A. Zehnder
The polarization data in hard X-ray and gamma-ray energy regimes remain until now very scarce. Having in mind very
large importance of the polarization information provided by astrophysical objects we propose a novel compact
polarimeter POLAR. It utilizes Compton scattering process and is based on the detector array made of low-Z, fast
scintillators. As the instrument with its relatively small dimensions and mass will be a non-intrusive one, it can be
installed on any typical satellite platform. It has a sensitivity peak in the energy range from tens to several hundreds keV
and a wide viewing angle covering almost a third of the sky. The main objects to be observed by POLAR will be
Gamma Ray Bursts and X-Ray Flashes but also X-ray pulsars (Crab). The instrument response and measurement
accuracy were intensively modeled and optimized in series of Monte Carlo simulations. It resulted in laboratory design
that consists of 2304 plastic scintillator bars with dimension 6x6x200 mm3. The scintillator light is converted by an
array of multi-anode photomultipliers. This arrangement assures both a large effective area for Compton scattering as
well as a big polarization modulation factor. Moreover, both quantities keep large values also for gammas coming off
the detector axis. Currently, a sequence of laboratory tests is performed using polarized photon sources of different
energies and various experimental setups. The first experiment consists of small (8x8) array of nominal scintillators
while the other one will utilize a large array (1536) of smaller bars (4x4x20 mm3) from the existing high energy project. The goal of these two measurements is to optimize the design, validate simulation results and test the prototype.
The MIRI is the mid-IR instrument for JWST and provides imaging, coronography and low and medium resolution spectroscopy over the 5-28μm band. In this paper we provide an overview of the key driving requirements and design status.
KEYWORDS: James Webb Space Telescope, Spectroscopy, Mirrors, Sensors, Electronics, Imaging systems, Optical components, Mid-IR, Optical filters, Picture Archiving and Communication System
MIRI is one of three focal plane instruments for the JWST covering the wavelengths region 5...28 μm. It is jointly developed by US and European institutes with the latter ones being responsible for the complete optical bench assembly, cryomechanisms, calibration source and the related electronics. MIRI is the combination of an imager with coronographic and low-resolution spectroscopic capabilities and a high-resolution integral-field spectrometer. These diverse options require several mechanisms to select a specific observing mode: (1) a filter wheel with bandpass filters, coronographic masks and a prism, (2) two grating/dichroic wheels with dispersing and order-sorting elements and (3) a flip mirror to direct the beam of an internal black body source into the spectrometer section. All mechanisms are required to operate under laboratory conditions (warm launch) as well as in the cryovacuum in space. The heat dissipation has to be small and the reliability and precision very high. Our low risk approach is the application of successfully qualified and flown components of the ISOPHOT (ISO) and PACS (HERSCHEL) instruments. We will report on the concept developed in phase B.
The primary scientific objective of RHESSI Small Explorer mission is to investigate the physics of particle acceleration and energy release in solar flares, through imaging and spectroscopy of X-ray/gamma-ray continuum and gamma-ray lines emitted by accelerated electrons and ions, respectively. RHESSI utilizes rotating modulator collimators together with cooled germanium detectors to image X-rays/gamma-rays from 3 keV to 17 MeV. It provides the first hard X-ray imaging spectroscopy, the first high resolution spectroscopy of solar gamma-ray liens, and the first imaging of solar gamma-ray lines and continuum. Here we briefly describe the mission and instrumentation, and illustrate its capabilities with solar and cosmic observations obtained in the first 17 months of operation.
The Reuven Ramaty High Energy Solar Spectroscopic Imager (RHESSI) is a
NASA Small Explorer satellite designed to study hard x-ray and
gamma-ray emission from solar flares. In addition, its
high-resolution array of germanium detectors can see photons
from high-energy sources throughout the Universe. Here we discuss
the various algorithms necessary to extract spectra, lightcurves,
and other information about cosmic gamma-ray bursts, pulsars,
and other astrophysical phenomena using an unpointed, spinning
array of detectors. We show some preliminary results and discuss
our plans for future analyses. All RHESSI data are public, and
scientists interested in participating should contact the
principal author.
Alex Zehnder, Jacek Bialkowski, F. Burri, Martin Fivian, Reinhold Henneck, A. Mchedlishvili, P. Ming, J. Welte, Knud Thomsen, David Clark, Brian Dennis, Gordon Hurford, David Curtis, Peter Harvey, David Pankow
RHESSI uses nine Rotating Modulation Collimators (RMCs) for imaging, each consisting of a pair of grids mounted on the rotating spacecraft. The angular resolutions range from 2.3 arcsec to 3arcmin. The relative twist between the two grids of each pair is the most critical parameter. It must be less than 20 arcsec for the finest grid. After precision alignment, it is monitored by the Twist Monitoring System (TMS) to a few arcsec. The Sun-pointing must be known better than 0.4 arcsec for the image reconstruction. This is achieved by the Solar Aspect System (SAS), which consists of a set of three Sun sensors. Each sensor is focusing the filtered Sun light onto a linear CCD. The onboard Aspect Data Processor (ADP) selects the 6 limb positions, which over-define the pointing offset of the Sun center in respect to the imaging axis of the imager. The Roll Angle System (RAS) continuously measures the roll angle of RHESSI within arcmin accuracy. The RAS is a continuously operating CCD star scanner. The time of the passage of a star image over the CCD is recorded and defines the roll angle, comparing its pixel position and amplitude with a star map.
Precise knowledge of the pointing and the roll angle of the rotating spacecraft is needed in order to reconstruct images with 2 arcsec resolution using the modulation patterns seen on each of the detectors of the bi-grid rotating collimators. Therefore, the aspect system consists of two subsystems of sensors, the Solar Aspect System (SAS) and Roll Angle System (RAS). The transmitted data consists of Solar limb data from the SAS (CCD pixels around the intersection of a Solar image with three linear CCDs) and Star event data from the RAS (CCD pixels induced by passages of Star images over a linear CCD). In order to meet the RHESSI requirements, the reconstructed pointing needs to be ≤ 0.4 arcsec (rms) relatively (≤ 1 arcsec absolutely) and the determination of the roll angle needs to be better than 1 arcmin (rms). Beside of understanding and calibrating each sensor, the error budget on the aspect system requires an alignment of the relevant features of the 1.55 m extended telescope on a micron level. This could be achieved by a combination of on-ground and in-flight calibration.
The activities during the instrument calibrations are summarized and first data are presented. The main instrument features, the line-spread function and the effective area, are discussed and the status of the in-flight calibrations is summarized.
Martin Fivian, Jacek Bialkowski, W. Hajdas, Reinhold Henneck, A. Mchedlishvili, P. Ming, Knud Thomsen, Alex Zehnder, Gordon Hurford, David Curtis, David Pankow, Brian Dennis
HESSI will image Solar flares with spatial resolution ranging from 2 and 190 arcsec over the energy range from 3 keV to approximately equals 100 keV and as low as 35 arcsec for energies up to 20 MeV, respectively. The system is based on Fourier- transform imaging in connection with high-resolution Ge- detectors. In order to achieve arcsec-quality images with an instrument having only arcmin alignment requirements one needs in addition two precise aspect systems: (1) The Solar Aspect System (SAS) will provide Sun aspect data with high precision (< 0.2 arcsec relative and 1 arcsec absolute) and at high frequency (100 Hz). It consists of three identical lens/filter assemblies with focus Sun images on three 2048 X (13 micrometers )2 linear CCDS at 1.55 m focal distance. Simultaneous exposures of three chords of the focused solar images are made and the pixels spanning each solar limb are recorded. (2) The Roll Angle System (RAS) will provide precise (arcmin) information on the roll angle of the rotating spacecraft. The RAS is a star scanner which points out radially and observes stars at 75 degrees from the Sun direction using a commercial lens and a fast CCD. The passage of a star image over the CCD will induce a signal in one or several pixels and the timing of this signal defines the roll angle, once the star has been identified by comparing its pixel position and amplitude with a star map. With a limiting magnitude of mv equals 3 we expect to observe at least 1 star per revolution (during direct Sun view) over 1 year; on the average we will detect about 10 stars/revolution. We report on the design, construction and calibration measurements of the SAS and RAS flight-model instruments.
KEYWORDS: Imaging systems, Imaging spectroscopy, Calibration, Solar energy, Solar processes, Modulation, Space operations, Spectroscopy, Spatial resolution, Hard x-rays
The primary object of HESSI is to study the explosive energy release in solar flares. HESSI will image flares with spatial resolution ranging between 2 and 35 arcseconds over the energy range 3 keV to 20 MeV. The system is based on Fourier-transform imaging in connection with high-resolution Ge-detectors. HESSI uses 9 Rotating Modulation Collimators, each consisting of a pair of widely separated (1.55 m) grids mounted on the rotating spacecraft. The grid pitches range from 34 micron to 2.75 mm in steps of sqrt(3). This gives angular resolutions that are spaced logarithmically from 2.3 arcseconds to 3 arcmin, allowing sources to be imaged over a wide range of angular scales. In our design the most critical performance parameter, the relative twist between the two grids of each pair--can be very precisely monitored on ground (on a level of several arcseconds) by a special Twist Monitoring System (TMS). Extensive measurements and cross-calibrations between the TMS and several coordinate measuring machines before and after the environmental tests demonstrated the precision and stability of the alignment to be on the order of 5 arcseconds.
Reinhold Henneck, Jacek Bialkowski, F. Burri, Martin Fivian, W. Hajdas, A. Mchedlishvili, P. Ming, Knud Thomsen, J. Welte, Alex Zehnder, Brian Dennis, Gordon Hurford, David Curtis, David Pankow
KEYWORDS: Charge-coupled devices, Sun, Imaging systems, Space operations, Solar energy, Fermium, Frequency modulation, Data processing, Light emitting diodes, Imaging spectroscopy
The HESSI SAS is a set of three Sun sensors, which shall provide high bandwidth information on the solar pointing of the rotating spacecraft. The precision of <EQ 0.4 arcsec relative is necessary in order to obtain the HESSI imaging resolution of 2 arcsec; the absolute accuracy of 1 arcsec is required for comparison with other measurements. Each SAS is based on focusing the Sun through a narrow bandwidth filter on to a 2048-element x (13(mu) )2 linear CCD. A digital threshold algorithm is used to select N pixels that span each solar limb for inclusion in the telemetry. Determination of the 6 limb crossing locations provided by the 3 subsystems defines the position offset of the Sun in the rotating frame. In this paper we describe the mechanical and electronic configuration of the SAS FM and the results of the first test measurements.
Reinhold Henneck, Jacek Bialkowski, F. Burri, Martin Fivian, W. Hajdas, A. Mchedlishvili, P. Ming, Knud Thomsen, J. Welte, Alex Zehnder, M. Dettwyler, F. Buerki, Gordon Hurford, David Curtis, David Pankow
The purpose of the HESSI RAS is to provide information on the roll angle of the rotation spacecraft. Precise knowledge of the roll angle is a necessary ingredient for image reconstruction. The RAS is a continuously operating star scanner that points out radially and observes stars at 75 degrees from the Sun direction using a commercial lens and a fast CCD. The passage of a star image over the CCD charges one or several pixels above threshold and the timing of this signal defines the roll angle, once the star has been identified by comparing its pixel position and amplitude with a star map. Roll angles at intermediate times are inferred by assuming uniform rotation. With a limiting star magnitude of mv equals 3 we expect to observe at least 1 star per revolution over 1 year; on the average we will detect about 10 stars/revolution.
Robert Lin, Gordon Hurford, Norman Madden, Brian Dennis, Carol Crannell, Gordon Holman, Reuven Ramaty, Tycho von Rosenvinge, Alex Zehnder, H. Frank van Beek, Patricia Bornmann, Richard Canfield, A. Gordon Emslie, Hugh Hudson, Arnold Benz, John Brown, Shinzo Enome, Takeo Kosugi, Nicole Vilmer, David Smith, Jim McTiernan, Isabel Hawkins, Said Slassi-Sennou, Andre Csillaghy, George Fisher, Chris Johns-Krull, Richard Schwartz, Larry Orwig, Dominic Zarro, Ed Schmahl, Markus Aschwanden, Peter Harvey, David Curtis, David Pankow, David Clark, Robert Boyle, Reinhold Henneck, Akilo Michedlishvili, Knud Thomsen, Jeff Preble, Frank Snow
The primary scientific objective of the High Energy Solar Spectroscopic Imager (HESSI) Small Explorer mission selected by NASA is to investigate the physics of particle acceleration and energy release in solar flares. Observations will be made of x-rays and (gamma) rays from approximately 3 keV to approximately 20 MeV with an unprecedented combination of high resolution imaging and spectroscopy. The HESSI instrument utilizes Fourier- transform imaging with 9 bi-grid rotating modulation collimators and cooled germanium detectors. The instrument is mounted on a Sun-pointed spin-stabilized spacecraft and placed into a 600 km-altitude, 38 degrees inclination orbit.It will provide the first imaging spectroscopy in hard x-rays, with approximately 2 arcsecond angular resolution, time resolution down to tens of ms, and approximately 1 keV energy resolution; the first solar (gamma) ray line spectroscopy with approximately 1-5 keV energy resolution; and the first solar (gamma) -ray line and continuum imaging,with approximately 36-arcsecond angular resolution. HESSI is planned for launch in July 2000, in time to detect the thousands of flares expected during the next solar maximum.
The x-ray multi-mirror (XMM) mission is the second of four cornerstone projects of the ESA long-term program for space science, Horizon 2000. The payload comprises three co- aligned high-throughput, imaging telescopes with a FOV of 30 arcmin and spatial resolution less than 20 arcsec. Imaging CCD-detectors (EPIC) are placed in the focus of each telescope. Behind two of the three telescopes, about half the x-ray light is utilized by the reflection grating spectrometer (RGS). The x-ray instruments are co-aligned and measure simultaneously with an optical monitor (OM). The RGS instruments achieve high spectral resolution and high efficiency in the combined first and second order of diffraction in the wavelength range between 5 and 35 angstrom. The design incorporates an array of reflection gratings placed in the converging beam at the exit from the x-ray telescope. The grating stack diffracts the x-rays to an array of dedicated charge-coupled device (CCD) detectors offset from the telescope focal plane. The cooling of the CCDs is provided through a passive radiator. The design and performance of the instrument are described below.
To follow up on the remarkable discoveries of the Compton Gamma Ray Observatory and GRANAT, the International Gamma Ray Astrophysics Laboratory (INTEGRAL) mission was selected by ESA as part of the agency's 'HORIZON 2000' strategic plan. It is scheduled to begin detailed gamma ray spectral and imaging studies, of unprecedented resolution, in the year 2001. One of the two main INTEGRAL instruments is a high performance imager. It features a coded aperture mask and a novel large area multilayer detector which utilizes both cadmium telluride and cesium iodide elements to deliver the fine angular-resolution approximately 12 arcmin, wide spectral response (15 keV to 10 MeV) and high resolution spectroscopy (6% at 100 keV) required to satisfy the mission's imaging objectives.
The Reflection Grating Spectrometer (RGS) onboard the ESA satellite XMM (X-ray Multi Mirror mission) combines a high resolving power (approximately 400 at 0.5 keV) with a large effective area (approximately 200 cm2). The spectral range selected for RGS (5 - 35 angstroms) contains the K shell transitions of N, O, Ne, Mg, Al, Si and S as well as the important L shell transitions of FE. The resolving power allows the study of a wide variety of challenging scientific questions. Detailed temperature diagnostics are feasible as the ionization balance is a unique function of the distribution of the electron temperature. Density diagnostics are provided by studying He-like triplets where the ratio of the forbidden to intercombination lines varies with density. Other fields of interest include the determination of elemental abundances, the study of optical depth effects, velocity diagnostics by measuring Doppler shifts and the estimate of magnetic fields through the observation of Zeeman splitting. The resolving power is obtained by an array of 240 gratings placed behind the mirrors of the telescope, dispersing about half of the X-rays in two spectroscopic orders. The X-rays are recorded by an array of 9 large format CCDs. These CCDs are operated in the frame transfer mode. They are back illuminated as the quantum efficiency of front illuminated devices is poor at low energies because of their poly-silicon gate structure. To suppress dark current the CCDs are passively cooled. In order to obtain the effective area of about 200 cm2, grating arrays and CCD cameras are placed behind two of the three XMM telescopes. A model of RGS was tested last autumn ('93) at the Panter long beam X-ray facility in Munich. The model consisted of a subset of four mirrors, eight representative gratings covering a small section of the inner mirror shells and a CCD camera containing three CCDs. The purpose of these tests was to verify the resolution and sensitivity of the instrument as a function of X-ray energy. Extensive simulations, using a Monte Carlo raytracing code, are used to interpret these tests. Preliminary results of these tests will be discussed and compared to the calculated response.
The basic principles of superconducting tunneling junction (STJ) detectors are summarized and the state of the art in experimental and simulation work involving STJ detectors is briefly examined. Astrophysical applications of STJ detectors are briefly addressed.
EUVITA, an array of eight extreme UV imaging telescopes with normal incidence reflection multilayer coated mirrors with central wavelengths of the individual telescopes between 50 and 250 A, is discussed. The scientific objectives of the EUVITA program are summarized and the instrument configuration and sensitivity are described. The detector electrons and command and the data handling system are briefly addressed.
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.