KEYWORDS: Calibration, James Webb Space Telescope, Stars, Point spread functions, Data modeling, Sensors, Astronomical interferometry, Equipment, Fourier optics, Astronomical interferometers
The multi-national James Webb Space Telescope (JWST) enables several new technologies, one of which is the first space-based infrared interferometer, the Aperture Masking Interferometry (AMI) mode of the Near Infrared Imager and Slitless Spectrograph (NIRISS). AMI is a niche but powerful tool for high resolution imaging of a variety of moderate- to high-contrast astronomical sources. The non-redundant mask (NRM) in the entrance pupil enables detection of structure below the classical Rayleigh diffraction limit, well inside the inner working angle of JWST’s coronagraphs. This explores a parameter space largely inaccessible to existing ground- and other space-based observatories. Early science observations leveraged the capabilities of this unique mode to observe dusty Wolf-Rayet binaries, spatially resolved solar system objects, massive exoplanet systems, and protoplanetary disks. The high quality of this space-based data demonstrated the need for improved analysis methods. We describe approaches to extracting interferometric observables, as well as pre- and post-extraction data cleaning routines we made available to the user community. We also discuss insights and unique challenges that were revealed during the commissioning, early calibration, and first science cycles of this promising observing mode: mitigation strategies for instrumental effects, lessons learned for optimizing observation configuration, and plans for ongoing calibration efforts. Knowledge gained from commissioning and calibration data – which are always non-proprietary – provide valuable insight into the capabilities and limitations of this mode, highlight areas that need improvement, and lay the groundwork for furthering JWST’s scientific objectives.
In less than a year, the James Webb Space Telescope (JWST) will inherit the mantle of being the world’s pre- eminent infrared observatory. JWST will carry with it an Aperture Masking Interferometer (AMI) as one of the supported operational modes of the Near-InfraRed Imager and Slitless Spectrograph (NIRISS) instrument. Aboard such a powerful platform, the AMI mode will deliver the most advanced and scientifically capable interferometer ever launched into space, exceeding anything that has gone before it by orders of magnitude in sensitivity. Here we present key aspects of the design and commissioning of this facility: data simulations (ami_sim), the extraction of interferometeric observables using two different approaches (IMPLANEIA and AMICAL), an updated view of AMI’s expected performance, and our reference star vetting programs.
The Near Infrared Imager and Slitless Spectrograph (NIRISS) Optical Simulator (NOS) is a
laboratory simulation of the single-object slitless spectroscopy and aperture masking interferometry modes of the
NIRISS instrument onboard the James Webb Space Telescope (JWST). A transiting exoplanet can be simulated
by periodically eclipsing a small portion (1% - 10ppm) of a super continuum laser source (0.4 μm - 2.4 μm) with
a dichloromethane filled cell. Dichloromethane exhibits multiple absorption features in the near infrared domain
hence the net effect is analogous to the atmospheric absorption features of an exoplanet transiting in front of its
host star. The NOS uses an HAWAII-2RG and an ASIC controller cooled to cryogenic temperatures. A separate
photometric beacon provides a flux reference to monitor laser variations. The telescope jitter can be simulated
using a high-resolution motorized pinhole placed along the optical path. Laboratory transiting spectroscopy data
produced by the NOS will be used to refine analysis methods, characterize the noise due to the jitter, characterize
the noise floor and to develop better observation strategies. We report in this paper the first exoplanet transit
event simulated by the NOS. The performance is currently limited by relatively high thermal background in the
system and high frequency temporal variations of the continuum source.
JWST’s Near-Infrared Imager and Slitless Spectrograph (NIRISS) includes an Aperture Masking Interferometry (AMI) mode designed to be used between 2.7μm and 4.8μm. At these wavelengths, it will have the highest angular resolution of any mode on JWST, and, for faint targets, of any existing or planned infrastructure. NIRISS AMI is uniquely suited to detect thermal emission of young massive planets and will permit the characterization of the mid-IR flux of exoplanets discovered by the GPI and SPHERE adaptive optics surveys. It will also directly detect massive planets found by GAIA through astrometric accelerations, providing the first opportunity ever to get both a mass and a flux measurement for non-transiting giant planets. NIRISS AMI will also enable the study of the nuclear environment of AGNs.
Accurate models of optical performance are an essential tool for astronomers, both for planning scientific observations ahead of time, and for a wide range of data analysis tasks such as point-spread-function (PSF)-fitting photometry and astrometry, deconvolution, and PSF subtraction. For the James Webb Space Telescope, the WebbPSF program provides a PSF simulation tool in a flexible and easy-to-use software package available to the community and implemented in Python. The latest version of WebbPSF adds new support for spectroscopic modes of JWST NIRISS, MIRI, and NIRSpec, including modeling of slit losses and diffractive line spread functions. It also provides additional options for modeling instrument defocus and/or pupil misalignments. The software infrastructure of WebbPSF has received enhancements including improved parallelization, an updated graphical interface, a better configuration system, and improved documentation. We also present several comparisons of WebbPSF simulated PSFs to observed PSFs obtained using JWST's flight science instruments during recent cryovac tests. Excellent agreement to first order is achieved for all imaging modes cross-checked thus far, including tests for NIRCam, FGS, NIRISS, and MIRI. These tests demonstrate that WebbPSF model PSFs have good fidelity to the key properties of JWST's as-built science instruments.
LLNL diamond machined a ZnSe grism for spectroscopy of transiting exoplanets on NIRISS, a Canadian instrument that
will fly on the James Webb Space Telescope. The grism operates over the wavelength range of 0.6 to 2.5 μm. It is cross-dispersed
by a ZnS prism and has a resolving power in first order of ~700. The surface error over the full 29 x 30 mm
grating aperture is 0.03 wave rms at 633nm. We measured a diffraction efficiency at 633 nm of 56% (nearly 88% after
accounting for Fresnel reflection). The diffraction pattern is clean with no discernible ghosts.
Grating prisms (grism) designed for near-infrared spectroscopy typically make use of high-refractive index materials such as zinc selenide (ZnSe), at the expense of large Fresnel losses ( 18%). Part of the loss can be recovered by using anti-reflection (AR) coatings. The technique is however considered risky when applied on the ruled surface of a grating, especially for a space application at cryogenic temperature. Such a grism, made of ZnSe and machined at Lawrence Livermore National Laboratory (LLNL) is mounted in the Near-Infrared Slitless Spectrograph (NIRISS) onboard the James Webb Space Telescope (JWST). Its Single Object Slitless Spectrograph (SOSS) observing mode uses the ZnSe grism and a cross-dispersing prism to produce R=700 spectra in orders 1 and 2 to cover the 0.6 to 2.5 microns spectral domain. The ZnSe grism is blazed at 1.23 microns, has a density of 54 lines/mm and its triangular grooves have a depth of 700 nm, a base of 18 microns, with facets angled at 1.9 degrees. Here, an AR coating produced by Thin Film Lab (TFL) and deposited on the ruled surface of a ZnSe grism sample was space qualified. Atomic force microscopy (AFM) showed no groove profile change pre/post coating despite the large relative thickness of the AR coating to that of the groove depth ( 35%). Also, the wavefront error map remained almost unchanged at lambda/8 (peak-to-valley at 632 nm) and survived unscathed through a series of three cryogenic cycles to 20 K. Finally, the transmission gain across our operating spectral range was almost as high as that for a unruled surface covered with the same AR coating (10-15%).
KEYWORDS: Interference (communication), Signal to noise ratio, Stars, Sensors, James Webb Space Telescope, Point spread functions, Data modeling, Electrons, Capacitance, Image processing
The James Webb Space Telescope Fine Guidance Sensor makes use of three 2048×2048 five micron cutoff H2RG HgCdTe detectors from Teledyne Imaging Systems. The FGS consists of two Guider channels and a Near-InfraRed Imager and Slitless Spectrograph (NIRISS) channel. We report here on detailed tests results from the Guider channels originating in both instrument level performance testing and from recent Guider performance testing with the FGS integrated into JWST’s Integrated Science Instrument Module (ISIM). A key performance parameter is the noise equivalent angle (NEA) or centroiding precision. The JWST requirement flowed down to the Guiders is a NEA of 4 milli-arcseonds, equivalent to approximately 1/20th of a detector pixel. This performance has been achieved in the testing to date. We have noted a systematic asymmetry in the NEA depending on whether the NEA in the row or column direction is considered. This asymmetry depends on guide star brightness and reaches its maximum, where the row NEA is 15% to 20% larger than the column NEA, at the dim end of the Guide star brightness range. We evaluate the detector level characteristics of spatially correlated noise and asymmetric inter-pixel capacitance (IPC) as potential sources of this NEA asymmetry. Modelling is used to estimate the impact on NEA of these potential contributors. These model results are then compared to the Guider test results obtained to date in an effort to isolate the cause of this effect. While asymmetric IPC can induce asymmetric NEA, the required magnitude of IPC is far greater than observed in these detectors. Thus, spatially correlated noise was found to be the most likely cause of the asymmetric NEA.
A new polarimeter has been built for the “Observatoire du Mont-Mégantic” (POMM) and is now in commissioning
phase. It will allow polarization measurements with a precision of 10-6, an improvement by a factor of 100 over the
previous observatory polarimeter. The characteristics of the instrument that allow this goal are briefly discussed and the
planned science observations are presented. They include exoplanets near their host star (hot Jupiters), transiting
exoplanets, stars with debris disks, young stars with proto-planetary disks, brown dwarfs, massive Wolf-Rayet stars and
comets. The details of the optical and mechanical designs are presented in two other papers.
KEYWORDS: Sensors, James Webb Space Telescope, Imaging systems, Staring arrays, Cadmium sulfide, Image processing, Data conversion, Detector arrays, Signal detection, Space telescopes
The James Webb Space Telescope Fine Guidance Sensor makes use of three 2048x2048 five micron cutoff HAWAII-2RG HgCdTe detectors from Teledyne Imaging Systems. The FGS consists of two Guider channels and a Near-InfraRed Imager and Slitless Spectrograph (NIRISS) channel. We report here on the characterization of the flight
detectors at the sub-system level and after integration to the flight instrument. The FGS-Guider has a number of unique
readout modes which are required to support observatory operations. Of critical importance is the identification and
classification of pixels which, if left unmasked or unprocessed, would compromise the guider performance. We report
on these classification methods and on the detailed behaviour of key bad pixel types which can impact guider
performance.
The Fine Guidance Sensor (FGS) is one of the four science instruments on board the James Webb Space Telescope (JWST). FGS features two modules: an infrared camera dedicated to fine guiding of the observatory and a science camera module, the Near-Infrared Imager and Slitless Spectrograph (NIRISS) covering the wavelength range between 0.7 and 5.0 μm with a field of view of 2.2' X 2.2'. NIRISS has four observing modes: 1) broadband imaging featuring seven of the eight NIRCam broadband filters, 2) wide-field slitless spectroscopy at a resolving power of rv150 between 1 and 2.5 μm, 3) single-object cross-dispersed slitless spectroscopy enabling simultaneous wavelength coverage between 0. 7 and 2.5 μm at Rrv660, a mode optimized for transit spectroscopy of relatively
bright (J > 7) stars and, 4) sparse aperture interferometric imaging between 3.8 and 4.8 μm enabling high
contrast ("' 10-4) imaging of M < 8 point sources at angular separations between 70 and 500 milliarcsec. This
paper presents an overview of the FGS/NIRISS design with a focus on the scientific capabilities and performance offered by NIRISS.
We present a new observing mode using WirCam on the Canada-France-Hawaii Telescope (CFHT). The staring mode with WIRCam can observe a target for several hours on the same pixels of the array. This allows for characterization of the photometric variations of the target to less than 0.02%, or to a signal-to-Noise Ratio ≥
5000. The technical challenges encountered to implement this mode are described as well as a simple model to estimate the idealized performance of this observing mode. Early results are also presented and compared to the models.
Persistence or image memory is a common problem in infrared array detectors. In WIRCam, the wide-field infrared
camera at the Canada France Hawaii Telescope, two of the four Hawaii-2RG (H2RG) HgCdTe imaging arrays in its
mosaic exhibit strong persistence while the other two do not. The dependence of the persistence on illumination flux
and fluence has been investigated and the persistence measured on the timescale of hundreds of milliseconds to several
hours. The goal of this work is to eventually provide an empirical model to correct for the persistence in image post-processing.
The Wide field Infrared Camera (WIRCam) is one of the 3 workhorse instruments in operation at CFHT. It's
mosaic of four HAWAII-2RG is read using two SDSU-III controllers with 32-amplifiers in parallel per detector.
First-light images showed that WIRCam suffered from three flavors of cross-talk: the "positive", "negative" and
"edge" cross-talks. All have now been eliminated at the source and WIRCam is now cross-talk free. Two of
these cross-talks originated from the controller electronic and one, the "edge" cross-talk, is intimately linked
to the HAWAII-2RG detector and its description may be of a broader interest for other instruments using
these detectors. We present the three cross-talk flavors and the hardware or software solutions implemented to
eliminate them.
CFHTs experience with interlacing science and guide pixel readout using the Hawaii-2RG infrared sensors on WIRCam has been problematic due to timing limitations inherent to this approach as well as unexpected behaviour in the sensors themselves. These problems have been overcome by implementing high-speed readout (1.4 s per read) for WIRCam's array of four Hawaii-2RG sensors, obviating the need for interlaced readout. The effect of the reset anomaly on the science and guide frames has been minimized by introducing suitable delays and a clocking scheme that does not significantly impact the minimum exposure time of the camera.
The Canada-France-Hawaii Telescope (CFHT) is now operating a Wide Field Infrared Camera (WIRCam) with a 20.5' x 20.5' field of view. The camera uses a mosaic of four Rockwell HAWAII-2RG detectors enabling subsample readouts at a rate of 50Hz for guiding and fast parallel readout of 32 amplifiers per detector for science. This paper will discuss the software architecture and implementation used to optimize the scientific productivity of the instrument as well as our experience during the first semester of use.
The Canada-France-Hawaii Telescope (CFHT) is commissioning a new Wide field Infrared Camera (WIRCam) that uses a mosaic of 4 HAWAII-2RG near- infrared detectors manufactured by Rockwell. At the heart of the instrument is an On-Chip Guiding System (OCGS) that exploits the unique parallel science/guide frame readout capability of the HAWAII-2RG detectors. A small sub sample of each array is continuously read at a rate of up to 50 Hz while the integration of the science image is ongoing with the full arrays (read at a maximal rate of 1.4 s per full frame). Each of these guiding windows is centered on a star to provide an error signal for the telescope guiding. An Image Stabilizer Unit (ISU) (i.e. a tip-tilt silica plate), provides the corrections. A Proportional Integral Differential (PID) closed loop controls the ISU such that telescope tracking is corrected at a rate of 5 Hz. This paper presents the technical architecture of the guiding system and performance measurements on the sky in engineering runs with WIRCam with faint stars up to magnitude 14.
The Canada-France-Hawaii Telescope (CFHT) is commissioning a new Wide
field Infrared Camera (WIRCam) that uses a mosaic of 4 HAWAII-2RG near-infrared detectors manufactured by Rockwell. At the heart of the instrument is an On-Chip Guiding System (OCGS) that exploits the unique parallel science/guide frame readout capability of the HAWAII-2RG detectors. A small subsample of each array is continuously read at a rate of 50 Hz while the integration of the science image is ongoing with the full arrays. Each of these guiding windows is centered on a star to provide an error signal for the telescope guiding. An Image Stabilizer Unit (ISU) (i.e. a tip-tilt silica plate), provides the corrections. A Proportional Integral Differential (PID) closed loop controls the ISU such that telescope tracking is corrected at a rate of 5 Hz. The guide window size and readout rate are adjustable but typical numbers are 8×8-16×16 boxes read at 50 or 1.5 Hz. This paper presents the technical architecture of the guiding system and performance measurements on the sky with WIRCam.
The Laboratoire d'Astrophysique Experimentale (LAE) at the Universite de Montreal has designed and built several near-infrared cameras/spectrometers in the last decade for the Observatoire du Mont-Mégantic (OMM), the Canada-France-Hawaii Telescope (CFHT) and the Herzberg Institute of Astrophysics (HIA). These instruments have required innovative solutions for cryogenic electro-mechanical controls. This paper presents cryogenic motors, bearings, gears, epoxies and positioning/sensing devices at the heart of these cryo-mechanisms. In particular, the paper will focus on a new ball plunger with integrated Hall effect sensor, which can be used both as a mechanical detent and analog position encoder.
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