This work forms part of The Hyperspectral Mission (THM) program, funded by the Canadian Space Agency. The designs correspond to three mission profiles with the parameters listed in Table 1. Two of the potential missions are designed for a flight on the EXPRESS external pallet of the International Space Station (ISS). All designs make use of push-broom imaging, whereby a slit is scanned across the scene by the orbitiil motion of the platform. In the case of the Enhanced ISS and Small Satellite designs there is an option to use ground motion compensation to reduce the ground sampling distance. There is also a common requirement for all the designs for a 0.4ftm to 2.5pm spectral waveband but there are varying requirements for instrument field, spatial and spectral resolution.
Patrick Côte, Alan Scott, Michael Balogh, Ron Buckingham, David Aldridge, Ray Carlberg, Weiguo Chen, Jean Dupuis, Clinton Evans, Laurent Drissen, Wes Fraser, Frederic Grandmont, Paul Harrison, John Hutchings, JJ Kavelaars, John-Thomas Landry, Christian Lange, Denis Laurin, Tarun Patel, Venka Pillay, Louis Piche, Andres Rader, Carmelle Robert, Marchin Sawicki, Robert Sorba, Guillaume Theriault, Ludovic Van Waerbeke
The Cosmological Advanced Survey Telescope for Optical and UV Research (CASTOR) is a proposed CSA
mission that would make a unique, powerful, and lasting contribution to astrophysics by providing panoramic,
high-resolution imaging in the UV/optical (0.15 - 0.55 μm) spectral region. This versatile `smallSAT'-class
mission would far surpass any ground-based optical telescope in terms of angular resolution, and would provide
ultra-deep imaging in three broad lters to supplement longer-wavelength data from planned international dark
energy missions (Euclid, WFIRST) as well as from the ground-based Large Synoptic Survey Telescope (LSST).
Combining the largest focal plane ever
own in space, with an innovative optical design that delivers HST-quality
images over a eld two orders of magnitude larger than Hubble Space Telescope (HST), CASTOR would image
about 1/8th of the sky to a (u-band) depth ~1 magnitude fainter than will be possible with LSST even after a
decade of operations. No planned or proposed astronomical facility would exceed CASTOR in its potential for
discovery at these wavelengths.
The Tunable Filter Imager of the James Webb Space Telescope will be based on blocking filters and a tunable Fabry-
Perot etalon with an average resolution of about 100. It will operate in two wavelength bands from 1.6 μm to 2.5 μm and
from 3.1 μm to 4.9 μm at a cryogenic temperature of about 35K. It will respectively be used to study the First Light and
re-ionization of the universe by surveying Lyman-alpha sources and to provide an in-depth study of proto-planetary
systems as well as giant planets of nearby stars.
The Tunable Filter Imager (TFI) is designed to image a sky field of view of 2.2' by 2.2' (magnified to 4.6 deg. x 4.6 deg.
at the etalon). Its tunable etalon has an aperture of 56 mm. It operates at low orders 1 and 3 for the two wavelength bands
which reduces the number of blocking filters to a number of eight. The etalon gap tuning between 2.5 μm and 5.5 μm is
provided by piezoelectric actuators and will be servo controlled by using capacitive displacement sensors.
In this paper, we present the etalon's opto-mechanical design that allows us to achieve the stringent requirements in
terms of resolution over a wide infrared wavelength band, and operation at low gap at cryogenic temperature. Cryogenic
test results will be shared as well.
The Fine Guidance Sensor (FGS) is part of the science instrumentation for the James Webb Space Telescope
(JWST). The FGS is required to operate at 37 K and provide the data needed to facilitate fine pointing and attitude
stabilization necessary to meet the requirements of the mission's science and engineering operations. We describe here
the selection of the proper optical design form to meet requirements and its relative merits. The FGS has progressed with
the successful completion of several key design reviews. The optical design of the current stage will be discussed here in
detail.
Previous publications for the JWST-FGS-TFI instrument described the design and fabrication of mirror coatings for
scanning Fabry-Perot etalons. Since that time, we have extended the fabrication process using ellipsometry analysis over
the full operational bandwidth from 1.0 to 5.0 microns for both mirror and anti-reflection coatings. This paper will
present single and multiple layer ellipsometry analysis of the a-Si/SiO2 optical properties. Analysis improvement came
from a-Si/SiO2 interface consideration and simultaneous use of ellipsometric data from Woollam V-VASE and IRVASE
instruments. Simulations of reflectance and transmittance based on the ellipsometric analysis results will also be
compared to spectrophotometric measurements for witness pieces.
KEYWORDS: Telescopes, Space telescopes, James Webb Space Telescope, Mirrors, Cryogenics, Optical spheres, Aluminum, Temperature metrology, Sensors, Wavefronts
The James Webb Space Telescope (JWST) Optical Telescope Element (OTE) gathers the light from astronomical
objects and provides it to four scientific instruments and the observatory guider. The Canadian contribution to JWST, the
Fine Guidance Sensor (FGS), includes both the FGS-Guider and one of the science instruments, the Tunable Filter
Imager (FGS-TFI); both are packaged together and are functionally independent. The FGS OGSE (Optical Ground
Support Equipment) is used to simulate the image from the OTE and verify the optical performance of the FGS Guider
and TFI during instrument level testing. The OGSE consists of 25 separate telescopes, each of which simulates a point
source at a different field location. The OGSE must maintain alignment and image quality at the cryogenic (30-40K)
operating temperature of the FGS. This paper presents WFE (wavefront error) testing for one of the telescopes over a
temperature range from ambient to cryogenic operating temperatures (30 K). This test made use of a Zygo
interferometer with the standard Zygo transmission sphere replaced by a custom-made transmission sphere located in the
cryo vacuum chamber. Meanwhile, image position displacements (focus) during cooling down with respect to ambient
are also obtained by tracking the position of the transmission sphere. The results show that the WFE degrades from 19
nm (RMS) at ambient to 42 nm (RMS) at 30 K, while the image displaces about 5.6 mm at 30 K with respect to ambient
temperature. The reason for the focus displacement is discussed.
KEYWORDS: Fabry–Perot interferometers, Electrochemical etching, Ferroelectric materials, James Webb Space Telescope, Sensors, Electronics, Tunable filters, Control systems, Reflectivity, Imaging systems
The Fine Guidance Sensor (FGS) on the James Webb Space Telescope (JWST) has a science observing capability
provided by the Tunable Filter Imager (TFI). The TFI incorporates dielectric coated Fabry-Perot etalon plates with a
small vacuum gap. The separation of the plates is controlled by the Etalon Control Electronics (ECE) board, using
piezoelectric actuators (PZTs) and capacitive displacement sensors (CDS). The TFI measures over the wavelength range
of 1.6 to 4.9 microns with a spectral resolution of R~100. We present the key components of the etalon system and the
approach for characterizing and testing the system. Initial results from assembly-level testing are also presented.
The Fine Guidance Sensor (FGS) of the James Webb Space Telescope (JWST) features a tunable filter imager (TFI)
module covering the wavelength range from 1.5 to 5.0 μm at a resolving power of ~100 over a field of view of
2.2'×2.2'. TFI also features a set of occulting spots and a non-redundant mask for high-contrast imaging. This paper
presents the current status of the TFI development. The instrument is currently under its final integration and test phase.
The Fine Guidance Sensor (FGS) is part of the instrument module for the James Webb Space Telescope (JWST). The
FGS operates at 37 K and provides feedback to correct motion blur caused by relative motion within the observatory - an
issue during long exposures. It also provides a tunable camera for science observations.
The FGS powered optics comprises three, Three Mirror Assembly (TMA) - style reflective systems - one with finite
conjugates and the remaining two are an infinite/finite conjugate pair. This paper addresses the issues of providing
traceable interferometric wave-front error measurements when the test optics are in a cryogenic vacuum chamber. To
meet space and time limits, we restrict attention to the finite conjugate device for the purposes of this publication.
The 'IMAKA (Imaging from MAuna KeA) instrument is a wide field visible light imager incorporating Ground Layer
Adaptive Optics (GLAO) to take maximum advantage of the excellent seeing available at the Canada-France-Hawaii
Telescope (CFHT). It requires better than 0.3" image quality simultaneously over a total field of view of approximately
one square degree (~3 x 10-4 sr). This requirement along with other criterions and constraints raises a challenge for
optical design. The advent of orthogonal transfer (OT) CCDs allows the tip-tilt portion of the atmospheric correction to
be performed at the science detector itself. 'IMAKA will take full advantage of the large array mosaics of OTCCDs.
Since the size of the adaptive mirror would drive the cost and hence implementation of the overall 'IMAKA instrument,
a review of possible optical design configurations which minimize the size (diameter) of the deformable mirror is
undertaken. A promising design was obtained and developed in more detail. This all reflective system is described along
with its predicted optical performance. An opto-mechanical design concept was developed around this nominal optical
design which takes into account various constraints due to its required location on the top end of the Canada France
Hawaii Telescope. The design concept is feasible and meets the optical performance requirements.
Earlier publications described a novel approach to the design of mirror coatings for scanning Fabry Perot etalons[1],[2]. Since that time, we have extended the design process, fabricated mirror coatings and used them to build etalons.
One design process improvement is the minimization of off-axis de-tuning. It can be significantly worse with a real mirror coating than the normal "blue shift" associated with the basic Fabry-Perot geometry. This option provides for the control of de-tuning in optimization. Another improvement is optimization for multiple-order operation of the etalon. This technique reduces etalon mirror travel while allowing tunability over a broad spectral range.
The focus of this paper, however, is the experimental results obtained for coatings and etalons built for the Fine Guidance Sensor-Tunable Filter Imager (FGS-TFI) - a Canadian Space Agency funded science instrument for the James Web Space Telescope (JWST). We present measured data for both the coating and the etalon performance.
We present the prototyping results and laboratory characterization of a narrow band Fabry-Perot etalon flight model
which is one of the wavelength selecting elements of the Tunable Filter Imager. The latter is a part of the Fine Guidance
Sensor which represents the Canadian contribution to NASA's James Webb Space Telescope. The unique design of this
etalon provides the JWST observatory with the ability to image at 30 Kelvin, a 2.2'x2.2' portion of its field of view in a
narrow spectral bandwidth of R~100 at any wavelength ranging between 1.6 and 4.9 μm (with a gap in coverage
between 2.5 and 3.2 μm). Extensive testing has resulted in better understanding of the thermal properties of the
piezoelectric transducers used as an actuation system for the etalon gap tuning. Good throughput, spectral resolution and
contrast have been demonstrated for the full wavelength range.
The James Webb Space Telescope (JWST) is a space-based, infrared observatory designed to study the early stages of
galaxy formation in the Universe. It is currently scheduled to be launched in 2013 and will go into orbit about the
second Lagrange point of the Sun-Earth system and passively cooled to 30-50 K to enable astronomical observations
from 0.6 to 28 μm. The JWST observatory consists of three primary elements: the spacecraft, the optical telescope
element (OTE) and the integrated science instrument module (ISIM). The ISIM Element primarily consists of a
mechanical metering structure, three science instruments and a fine guidance sensor with significant scientific capability.
One of the critical opto-mechanical alignments for mission success is the co-registration of the OTE exit pupil with the
entrance pupils of the ISIM instruments. To verify that the ISIM Element will be properly aligned with the nominal
OTE exit pupil when the two elements come together, we have developed a cryogenic pupil measurement test
architecture to measure three of the most critical pupil degrees-of-freedom during optical testing of the ISIM Element.
The pupil measurement scheme makes use of: specularly reflective pupil alignment references located inside of the
JWST instruments; ground support equipment that contains a pupil imaging module; an OTE simulator; and pupil
viewing channels in two of the JWST flight instruments. Current modeling and analysis activities indicate this
measurement approach will be able to verify pupil shear to an accuracy of 0.5-1%.
The Fine Guidance Sensor (FGS) of the James Webb Space Telescope (JWST) features a tunable filter imager (TFI)
module covering the wavelength range from 1.6 to 4.9 μm at a resolving power of ~100 over a field of view of
2.2'x2.2'. TFI also features a set of 4 occulting spots for coronagraphy. A review of the current design and development
status of TFI is presented along with two key TFI science programs: the detection of first light, high-redshift Lyα
emitters and the detection/characterization of exoplanets.
KEYWORDS: Point spread functions, Stars, James Webb Space Telescope, Performance modeling, Observatories, Sensors, Electronics, Mirrors, Monte Carlo methods, Data modeling
The Engineering Test Unit (ETU) of the Fine Guidance Sensor (FGS) for the James Webb Space Telescope (JWST) is
currently in fabrication. Extensive modeling of the key FGS-Guider performance parameters has been used throughout
the design process and continues to be used to evaluate the expected performance of the as-built instrument. A key
parameter of interest is the expected Noise Equivalent Angle (NEA) provided by the FGS. The NEA will, in part,
determine the ultimate image quality of the JWST Observatory. In this paper we use updated estimates of the End-oflife
impact of contamination to present the current expected NEA performance of the FGS flight model. As component
test data becomes available this data will be used as input to the FGS NEA performance model to assess the expected
performance of the instrument.
The scanning Fabry Perot interferometer may be tuned over a considerable spectral waveband by adjusting the gap between the mirrors. However, a wide tuning range places significant demands on the design of the mirror coatings. The coatings should be all-dielectric for low absorption. They must also provide good reflectance and phase control over the tuning range.
In general, both the reflectance and the phase-shift on reflection of dielectric mirrors are dispersive. This dispersion, left uncontrolled, changes the spectral resolution of a scanning Fabry Perot interferometer over the operating waveband. The mirror phase dispersion also reduces the free spectral range must be controlled in the design process to achieve operation with a reasonable number of blocking filters.
However, some phase dispersion will always be present in the mirror design. It is, therefore, desirable to tune the reflectance dispersion and the remaining phase dispersion so that the combination stabilizes the spectral resolution.
This paper describes a suitable optimization method. It takes advantage of some features of the Fabry Perot equations to provide error terms for mirror optimization that target a specific spectral resolution value. The paper includes the theory and provides some numerical examples.
The James Webb Space Telescope (JWST) Observatory, the follow-on mission to the Hubble Space Telescope and to the Spitzer Space Facility, will yield astounding breakthroughs in the realms of infrared space science. The science instrument suite for this Observatory will consist of a Near-Infrared Camera, a Near-Infrared Spectrograph, a Mid-Infrared Instrument with imager, coronagraph and integral field spectroscopy modes, and a Fine Guider System Instrument with both a Guider module and a Tunable Filter Module. In this paper we present an overview of the optical designs of the telescope and instruments.
The Fine Guider Sensor (FGS) of the James Webb Space Telescope (JWST) features two tunable filter (R~100) modules covering the 1.2-2.4 μm and 2.4-4.8 μm wavelength ranges, respectively. A set of occulting spots/bars mounted on a small slide located at the edge of the 2.3’x 2.3’ field of view (FOV) along with apodizing masks located in the filter wheel of each channel enable coronagraphic operation. Each coronagraphic field covers a square FOV of 20”x20”. The FGS-TF coronagraph complements the coronagraphic capabilities implemented in NIRCam and MIRI. This paper presents numerical simulations to predict the high-contrast imaging performance of the FGS-TF coronagraph. The combined coronagraphic and differential spectral imaging capabilities of the FGS-TF constitute a powerful tool for detecting and characterizing exoplanets with JWST.
The Canadian contribution to the James Webb Space Telescope (JWST) mission will be the Fine Guidance Sensor (FGS), incorporating a science-observing mode using tunable filters. We describe here the requirements, the opto-mechanical design concept and bread-board test results for the JWST FGS tunable filters. The FGS requires two continuously tunable filters over the wavelength ranges 1.2 - 2.4 microns and 2.4 - 4.8 microns each having a spectral resolution in the range of R~70 to 200. The selected implementation uses dielectric coated Fabry-Perot etalon plates with a small air gaps. The design finesse is ~30 and the filters are used in 3rd order. The operating temperature is ~35K. Current coating designs provide implementations that require only five blocking filters in each wavelength range to suppress unwanted orders. The filters will be scanned via the use of low voltage piezo-electric transducers. We present results from cryogenic tests of coating samples, PZT actuators and a structural model. The PZT actuators were found have a displacement of ~3.3 microns at 30K with an applied voltage of 125V, more than sufficient for the required scan of the Fabry-Perot plate spacing. The prototype etalon coating was found to be very stable cryogenically, having a measured change of transmission of only ~1% at 77K. The same coating on a 12.7 mm thick substrate, similar to that planned for the filter, was found to have a 18 nm peak-to-valley surface figure change when cooled to 30K. These results demonstrate that the development of tunable filters for the JWST FGS is on track to meet the technology readiness requirements of the program.
KEYWORDS: Tunable filters, James Webb Space Telescope, Sensors, Electronics, Mirrors, Stars, Space operations, Interfaces, Control systems, Optical filters
The science instrumentation for the James Webb Space Telescope (JWST) has concluded its Phase A definition stage. We have developed a concept for the JWST Fine Guidance Sensor (FGS), which will form the Canadian contribution to the mission. As part of the JWST re-plan in early 2003, the FGS design was recast to incorporate a narrow-band (R~100) science-imaging mode. This capability was previously resident in the NIRCam instrument. This FGS science mode makes use of tunable filters and filter wheels containing blocking filters, calibration sources and aperture masks. The science function of the FGS Tunable Filters (FGS-TF) remains complementary to the NIRCam science goals. Narrow-band FGS-TF imaging will be employed during many of the JWST deep imaging surveys to take advantage of the sensitivity to emission line objects. The FGS-TF will also provide a coronagraphic capability for the characterization of host galaxies of active galactic nuclei and for the characterization of extra solar planets. The primary function of the FGS remains to provide the sensor data for the JWST Observatory line-of-sight stabilization system. We report here on the overall configuration of the FGS and we indicate how the concept meets the performance and interface requirements.
The Damped Least Squares (DLS) optimization algorithm plays a useful role in the design of multilayer optical coatings.
It does, however, require numerically well-behaved error terms and the convergence is highly dependent on the degree of
non-linearity present in the error term chosen.
This paper makes some recommendations for the choice of error terms for effective control of phase-dispersion in dielectric mirrors.
Diamond-turning as a manufacturing method for infrared optics opens new possibilities for solving packaging problems. Optical surfaces and mechanical mounting features may be related to one another to reduce design complexity, tolerance accumulation, and cost.
The measurement of pollution in the troposphere (MOPITT), is an experiment on the earth observing satellite, scheduled for launch in 1999. The instrument is an infrared spectrometer which will measure concentrations of carbon monoxide and methane in the atmosphere. This paper describes the optical mechanical design for the MOPITT qualification model lens systems.
The design of two advanced underwater lenses for use with high-resolution, charged coupled device (CCD) still cameras is presented. Some practical aspects of lenses for CCD cameras are discussed and how the customer's requirements led to different choices of water-lens interface is demonstrated.
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