The James Webb Space Telescope (JWST) launched on December 25, 2021, and its optical performance in orbit has been even better than predicted pre-flight. The static wavefront error (WFE) is less than half the value specified for the requirement of having diffraction-limited image quality at 2 microns in the NIRCam shortwave channel, enabling the observatory to deliver both sharper images and higher sensitivity than anticipated. In addition to the excellent image quality, the optical stability has also exceeded expectations, both in terms of high-frequency dynamic contributions (which would be perceived as part of “static WFE”) and in terms of drifts over minutes, hours, and days. Stability over long timescales is critical for several important science cases, including exoplanet transit spectroscopy and coronagraphy. JWST’s stability success was achieved through detailed design and testing, with several important lessons learned for future observatories, especially the Habitable Worlds Observatory that is expected to need even higher levels of stability. We review the stability architecture, how it was technologically demonstrated, the ground test results and improvements, the on-orbit results, and the lessons learned.
KEYWORDS: Telescopes, James Webb Space Telescope, Image segmentation, Observatories, Mirrors, Space operations, Space telescopes, Galactic astronomy, Wavefronts, Stars
The James Webb Space Telescope (Webb) is a large, infrared space telescope that recently completed its on-orbit commissioning activities and has now embarked on its first year of approved science. Its architecture includes many first-of-its kind innovations for space, including a segmented primary mirror that is 6.6 m in diameter and a 5-layer sunshield used to passively cool the telescope and its four science instruments. Although Webb had an extensive test program, the system-level performance often relied on predictions based on integrated modeling, using conservative factors for the model uncertainties and primarily focusing on evaluating the performance at the end of life. A set of commissioning activities were designed for a system-level characterization of the performance. This proceeding will provide the status of the mission, including a discussion of the major events, on-orbit system performance, and early science highlights.
Backgrounds observed by JWST will be a critical parameter for overall observatory sensitivity. JWST’s background, sensitivity and other performance requirements drove the observatory’s open architecture, sunshield geometry, orbit at L2 and other unique characteristics. These requirements were verified by analysis, to be measured for the first time on-orbit. Modeling JWSTs backgrounds is complex, as JWST backgrounds have multiple components including: backgrounds from in-field sources (such as Zodiacal Light) and stray light from scattering of sky sources outside the field; thermal selfemission of optical surfaces; and scattering of thermal self-emission from other Observatory surfaces. The unbaffled telescope design allows stray light paths from multiple directions. The 5-layer sunshield passively cools and shades the telescope and science instruments; however, there are thermal paths that may affect thermal performance. In-field backgrounds and stray light from sky sources can depend on the telescope’s pointing and observation date. The thermal emission contributions will depend on the Observatory’s sun orientation and recent history. The JWST Background Tool (JBT) uses the stray light models, in-field backgrounds, and thermal models to predict the expected backgrounds. Onorbit, several positions were measured at multiple wavelengths with NIRCam and MIRI to probe JWST’s backgrounds and validate model predictions. These results may be used to update the JWST Exposure Time Calculator in preparation for the Cycle 2 proposal call. This conference proceeding will provide a summary of the modeling backgrounds and report on the measured on-orbit backgrounds.
KEYWORDS: James Webb Space Telescope, Control systems, Calibration, Mirrors, Telescopes, Temperature metrology, Space telescopes, Interferometers, Metrology, Data modeling
The Astro 2020 Decadal Survey has recommended technology and pre-formulation efforts for a 6-meter class Ultraviolet Optical Infrared telescope which is stable for high contrast observations of Exoplanets and general astrophysics. Here we report on progress on an ultra-stable test system and a series of picometer scale metrology demonstrations using High Speed Interferometry to achieve new levels of thermal control and new methods of calibration along with small scale demonstrations of mirror and structure components. Here we review the history of these efforts and recent ultra-stable measurements of a glass test article including thermal control and optical stability. We will summarize the challenge and progress of making drift measurements and report on recent progress in thermal control and glass ultrastability control that could have implications for future systems. We will close with a discussion of implications of these results to future efforts.
The James Webb Space Telescope (JWST) is a segmented deployable telescope, currently operating at L2. The telescope utilizes 6 degrees of freedom for adjustment of the Secondary Mirror (SM) and 7 degrees of freedom for adjustment of each of its 18 segments in the Primary Mirror (PM). After deployment, the PM segments and the SM arrived in their correct optical positions to within a ~1 mm, with accordingly large wavefront errors. A Wavefront Sensing and Controls (WFSC) process was executed to adjust each of these optical elements in order to correct the deployment errors and produce diffraction-limited images across the entire science field. This paper summarizes the application of the WFSC process.
The James Webb Space Telescope (JWST) is a large (6.5 m) near- and mid-infrared telescope scheduled for launch in 2021. JWST will be used to explore fundamental questions in astrophysics and planetary science, including the evolution of galaxies, the first light of stars, the formation of stars and planets as well as the characterization of exoplanets. To achieve these scientific goals, NASA and its international partners, the Canadian Space Agency (CSA) and the European Space Agency (ESA), have developed four science instruments for JWST and have prepared detailed commissioning plans for each. The NASA Project Science team has also outlined activities to characterize the performance of the Observatory as a whole. These activities include: 1) monitoring of the instrument and telescope cooldown for contamination mitigation; 2) measurements of straylight and other backgrounds for validation of the JWST stray light models as well as instrument background subtraction algorithms; 3) characterization of optical thermal distortion between its hot and cold telescope pointings within the observable field of regard and 4) trending of observatory performance parameters. Each of these activities has been planned in close collaboration with the observatory wavefront, commissioning planning, and science instrument teams. Here we present the plans for these activities, the expected results and how they will impact future guest observer (GO) proposals and JWST science community.
KEYWORDS: James Webb Space Telescope, Aerospace engineering, Space operations, Space telescopes, Mid-IR, Observatories, Mirrors, Infrared telescopes, Optical telescopes, Imaging systems
The James Webb Space Telescope (Webb) is the largest space telescope realized to-date, with a 6.5 m segmented primary mirror that must be folded to fit within its Ariane 5 launcher fairing. This infrared telescope is passively cooled using a five-layer sunshield that will keep the optical telescope and its four science instruments in the shade throughout the lifetime of the mission in an L2 orbit. Webb's science instruments include near- and mid- infrared imagers and spectrometers that cover the spectral range from 0.6-28.5 μ.m The Webb mission has a long history with numerous first of its kind technology developments, ground support equipment innovations, and algorithmic characterization advances. This conference proceeding summarizes the technical progress over the past two years, from the Spacecraft Element environmental testing to the Observatory integration and testing, and the final Observatory test plans leading up to launch, on-orbit commissioning, and science operations.
The James Webb Space Telescope (JWST) is a NASA flagship mission that will address multiple science themes including our Universe’s first light, the assembly of galaxies, the birth of stars and planetary systems, and planets and the origins of life. The JWST is a large (6.5 m) segmented aperture telescope equipped with near- and mid-infrared instruments (0.6-28 microns), all of which are passively cooled to ~40 K by a 5-layer sunshield while the mid-infrared instrument is actively cooled to 7 K. The JWST will be launched to an L2 orbit aboard a European Space Agency (ESA) supplied Ariane 5 rocket, whose payload volume constraints require that the JWST structure is stowed for launch. The JWST telescope recently completed its cryogenic test program and the sunshield has been fully integrated and deployed. JWST is currently in the final stages of the test program at the Observatory level. The current estimated JWST performance metrics will be presented, such as the image quality, pointing stability, sensitivity, and stray light backgrounds. The JWST development status and future plans will be described for the final testing, launch, and commissioning. JWST is an international project with contributions from NASA, ESA, and the Canadian Space Agency (CSA). Northrop Grumman Aerospace Systems is the prime contractor for the JWST, and the Space Telescope Science Institute will serve as the science operations center.
Future large astronomical telescopes in space will have architectures that expose the optics to large angular extents of the sky. Options for reducing stray light coming from the sky range from enclosing the telescope in a tubular baffle to having an open telescope structure with a large sunshield to eliminate solar illumination. These two options are considered for an on-axis telescope design to explore stray light considerations. A tubular baffle design will limit the sky exposure to the solid angle of the cone in front of the telescope set by the aspect ratio of the baffle length to Primary Mirror (PM) diameter. Illumination from this portion of the sky will be limited to the PM and structures internal to the tubular baffle. Alternatively, an open structure design will allow a large portion of the sky to directly illuminate the PM and Secondary Mirror (SM) as well as illuminating sunshield and other structure surfaces which will reflect or scatter light onto the PM and SM. Portions of this illumination of the PM and SM will be scattered into the optical train as stray light. A Radiance Transfer Function (RTF) is calculated for the open architecture that determines the ratio of the stray light background radiance in the image contributed by a patch of sky having unit radiance. The full 4π steradian of sky is divided into a grid of patches, with the location of each patch defined in the telescope coordinate system. By rotating the celestial sky radiance maps into the telescope coordinate frame for a given pointing direction of the telescope, the RTF may be applied to the sky brightness and the results integrated to get the total stray light from the sky for that pointing direction. The RTF data generated for the open architecture may analyzed as a function of the expanding cone angle about the pointing direction. In this manner, the open architecture data may be used to directly compare to a tubular baffle design parameterized by allowed cone angle based on the aspect ratio of the tubular baffle length to PM diameter. Additional analysis has been done to examine the stray light implications for the fields near the image of a bright source. This near field stray light is shown to be dependent on the Bidirectional Reflectance Distribution Function (BRDF) characteristics of the mirrors in the optical train. The near field stray light contribution is dominated by those mirrors closer to the focal plane compared to the contributions from the PM and SM. Hence the near field stray light is independent of the exterior telescope baffle geometry. Contributions from self-emission from the telescope have been compared to natural background for telescopes operating at infrared wavelengths.
KEYWORDS: James Webb Space Telescope, Optical components, Space telescopes, Optical testing, Sensors, Calibration, Data modeling, Human-machine interfaces, Error analysis, Analytical research
NASA’s James Webb Space Telescope (JWST) is a 6.5m diameter, segmented, deployable telescope for cryogenic IR space astronomy. The JWST Observatory includes the Optical Telescope Element (OTE) and the Integrated Science Instrument Module (ISIM), that contains four science instruments (SI) and the Fine Guidance Sensor (FGS). The SIs are mounted to a composite metering structure. The SIs and FGS were integrated to the ISIM structure and optically tested at NASA's Goddard Space Flight Center using the Optical Telescope Element SIMulator (OSIM). OSIM is a full-field, cryogenic JWST telescope simulator. SI performance, including alignment and wavefront error, was evaluated using OSIM. We describe test and analysis methods for optical performance verification of the ISIM Element, with an emphasis on the processes used to plan and execute the test. The complexity of ISIM and OSIM drove us to develop a software tool for test planning that allows for configuration control of observations, implementation of associated scripts, and management of hardware and software limits and constraints, as well as tools for rapid data evaluation, and flexible re-planning in response to the unexpected. As examples of our test and analysis approach, we discuss how factors such as the ground test thermal environment are compensated in alignment. We describe how these innovative methods for test planning and execution and post-test analysis were instrumental in the verification program for the ISIM element, with enough information to allow the reader to consider these innovations and lessons learned in this successful effort in their future testing for other programs.
The formation of water ice on key thermal and optical surfaces is a factor in the design of the
James Webb Space Telescope. Many of these concerns are related to the mid-infrared stray
light performance of the system. In this paper, an expression for the radiance of a
contaminated surface is formulated, including directional, film thickness and cooling effects.
The resulting formula is then evaluated to show how radiance emanating from the surface
changes for various thicknesses of the ice layer as a function wavelength and the local thermal
environment. This paper concludes with an analysis and discussion of this complex behavior.
KEYWORDS: Stray light, Phase modulation, Observatories, James Webb Space Telescope, Near infrared, Space telescopes, Telescopes, Adaptive optics, Mirrors, Aerospace engineering
The James Webb Space Telescope (JWST) is a large cryogenic telescope observing over a spectral range from 0.6 μm to 29 μm. A large sun shield blocks sunlight and provides thermal isolation for the optics. Analyses characterizing the stray light reaching the instrument focal planes from the galactic sky, zodiacal background, bright objects near the line-of-sight, and earth and moon shine are presented along with the self-generated thermal infrared background from Observatory structures. The latter requires thermal analysis to characterize the Observatory temperatures. Dependencies on the surface properties of BRDF and emittance are discussed for the underlying materials and the effects of contamination
KEYWORDS: James Webb Space Telescope, Mirrors, Particles, Contamination, Aluminum, Reflectivity, Aerospace engineering, Telescopes, Stray light, Picture Archiving and Communication System
The James Webb Telescope (JWST) is a large cryo-optical system. Many critical thermal control
or optical surfaces are exposed to ground and flight environments and are expected to be contaminated to
some level. In order to calculate key system performance parameters, such as stray light and radiative
thermal transfer, the emissivity must be known in terms of contamination level and temperature. This
paper will introduce the methods of determining these emissivities, and the discussion will cover the types
of particulate and molecular contamination expected on JWST. The results of the calculations will be
introduced and discussed.
Disordered thin film SiO2/SiOx coatings undergoing electron-beam bombardment exhibit cathodoluminescence, which can produce deleterious stray background light in cryogenic space-based astronomical observatories exposed to high energy electron fluxes from space plasmas. As future observatory missions push the envelope into more extreme environments and more complex and sensitive detection, a fundamental understanding of the dependencies of this
cathodoluminescence becomes critical to meet performance objectives of these advanced space-based observatories.
Measurements of absolute radiance and emission spectra as functions of incident electron energy, flux, and power
typical of space environments are presented for thin (~60-200 nm) SiO2/SiOx optical coatings on reflective metal substrates over a range of sample temperatures (~40-400 K) and emission wavelengths (~260-5000 nm). Luminescent
intensity and peak wavelengths of four distinct bands were observed in UV/VIS/NIR emission spectra, ranging from 300
nm to 1000 nm. A simple model is proposed that describes the dependence of cathodoluminescence on irradiation time,
incident flux and energy, sample thickness, and temperature.
Electron irradiation experiments have investigated the diverse electron-induced optical and electrical signatures observed
in ground-based tests of various space observatory materials at low temperature. Three types of light emission were
observed: (i); long-duration cathodoluminescence which persisted as long as the electron beam was on (ii) short-duration
(<1 s) arcing, resulting from electrostatic discharge; and (iii) intermediate-duration (~100 s) glow—termed “flares”. We
discuss how the electron currents and arcing—as well as light emission absolute intensity and frequency—depend on
electron beam energy, power, and flux and the temperature and thickness of different bulk (polyimides, epoxy resins,
and silica glasses) and composite dielectric materials (disordered SiO2 thin films, carbon- and fiberglass-epoxy
composites, and macroscopically-conductive carbon-loaded polyimides). We conclude that electron-induced optical
emissions resulting from interactions between observatory materials and the space environment electron flux can, in
specific circumstances, make significant contributions to the stray light background that could possibly adversely affect
the performance of space-based observatories.
James Webb Space Telescope (JWST) Optical Telescope Element (OTE) mirror coating program has been completed.
The science goals of the JWST mission require a uniform, low stress, durable optical coating with high reflectivity over
the JWST spectral region. The coating has to be environmentally stable, radiation resistant and compatible with the
cryogenic operating environment. The large size, 1.52 m point to point, light weight, beryllium primary mirror (PM)
segments and flawless coating process during the flight mirror coating program that consisted coating of 21 flight
mirrors were among many technical challenges. This paper provides an overview of the JWST telescope mirror coating
program. The paper summarizes the coating development program and performance of the flight mirrors.
The James Webb Space Telescope (JWST) is a segmented deployable telescope, utilizing 6 degrees of freedom for
adjustment of the Secondary Mirror (SM) and 7 degrees of freedom for adjustment of each of its 18 segments in the
Primary Mirror (PM). When deployed, the PM segments and the SM will be placed in their correct optical positions to
within a few mm, with accordingly large wavefront errors. The challenge, therefore, is to position each of these optical
elements in order to correct the deployment errors and produce a diffraction-limited telescope, at λ=2μm, across the
entire science field. This paper describes a suite of processes, algorithms, and software that has been developed to
achieve this precise alignment, using images taken from JWST’s science instruments during commissioning. The results
of flight-like end-to-end simulations showing the commissioning process are also presented.
NASA's Technology Readiness Level (TRL)-6 is documented for the James Webb Space Telescope (JWST) Wavefront
Sensing and Control (WFSC) subsystem. The WFSC subsystem is needed to align the Optical Telescope Element
(OTE) after all deployments have occurred, and achieves that requirement through a robust commissioning sequence
consisting of unique commissioning algorithms, all of which are part of the WFSC algorithm suite. This paper identifies
the technology need, algorithm heritage, describes the finished TRL-6 design platform, and summarizes the TRL-6 test
results and compliance. Additionally, the performance requirements needed to satisfy JWST science goals as well as the
criterion that relate to the TRL-6 Testbed Telescope (TBT) performance requirements are discussed.
The Telescope to Observe Planetary Systems (TOPS) is a proposed space mission to image planetary systems of
nearby stars simultaneously in a few wide spectral bands covering the visible light (0.4-0.9 μm). It achieves its
power by combining a high accuracy wavefront control system with a highly efficient Phase-Induced Amplitude
Apodization (PIAA) coronagraph which provides strong suppression very close to the star (within 2 λ/D). The
PIAA coronagraphic technique opens the possibility of imaging Earthlike planets in visible light with a smaller
telescope than previously supposed. If sized at 1.2-m, TOPS would image and characterize many Jupiter-sized
planets, and discover 2 RE rocky planets within habitable zones of the ≈10 most favorable stars. With a larger
2-m aperture, TOPS would have the sensitivity to reveal Earth-like planets in the habitable zone around ≈20
stars, and to characterize any found with low resolution spectroscopy. Unless the occurrence of Earth-like planets
is very low (η⊕ <~ 0.2), a useful fraction of the TPF-C scientific program would be possible with aperture much
smaller than the baselined 8 by 3.5m for TPF, with its more conventional coronagraph. An ongoing laboratory
experiment has successfully demonstrated high contrast coronagraphic imaging within 2 λ/d with the PIAA
coronagraph / focal plane wavefront sensing scheme envisioned for TOPS.
The Telescope to Observe Planetary Systems (TOPS) is a proposed space mission to image in the visible (0.4-
0.9 μm) planetary systems of nearby stars simultaneously in 16 spectral bands (resolution R≈20). For the
≈10 most favorable stars, it will have the sensitivity to discover 2RΕ rocky planets within habitable zones and
characterize their surfaces or atmospheres through spectrophotometry. Many more massive planets and debris
discs will be imaged and characterized for the first time. With a 1.2m visible telescope, the proposed mission
achieves its power by exploiting the most efficient and robust coronagraphic and wavefront control techniques.
The Phase-Induced Amplitude Apodization (PIAA) coronagraph used by TOPS allows planet detection at 2λ/d
with nearly 100% throughput and preserves the telescope angular resolution. An efficient focal plane wavefront
sensing scheme accurately measures wavefront aberrations which are fed back to the telescope active primary
mirror. Fine wavefront control is also performed independently in each of 4 spectral channels, resulting in a
system that is robust to wavefront chromaticity.
Terrestrial Planet Finder Coronagraph, one of two potential architectures, is described. The telescope is designed to make a visible wavelength survey of the habitable zones of at least thirty stars in search of earth-like planets. The preliminary system requirements, optical parameters, mechanical and thermal design, operations scenario and predicted performance is presented. The 6-meter aperture telescope has a monolithic primary mirror, which along with the secondary tower, are being designed to meet the stringent optical tolerances of the planet-finding mission. Performance predictions include dynamic and thermal finite element analysis of the telescope optics and structure, which are used to make predictions of the optical performance of the system
Detection of extra-solar, and especially terrestrial-like planets, using coronagraphy requires an extremely high level of wavefront correction. For example, the study of Woodruff et al. (2002) has shown that phase uniformity of order 10-4λ(rms) must be achieved over the critical range of spatial frequencies to produce the ~1010 contrast needed for the Terrestrial Planet Finder (TPF) mission. Correction of wavefront phase errors to this level may be accomplished by using a very high precision deformable mirror (DM). However, not only phase but also amplitude uniformity of the same scale (~10-4) and over the same spatial frequency range must be simultaneously obtained to remove all residual speckle in the image plane. We present a design for producing simultaneous wavefront phase and amplitude uniformity to high levels from an input wavefront of lower quality. The design uses a dual Michelson interferometer arrangement incorporating two DM and a single, fixed mirror (all at pupils) and two beamsplitters: one with unequal (asymmetric) beam splitting and one with symmetric beam splitting. This design allows high precision correction of both phase and amplitude using DM with relatively coarse steps and permits a simple correction algorithm.
A method of coarse phasing segmented mirrors using white light interferometry (WLI) has been developed for the Next Generation Space Telescope (NGST) wavefront sensing and control. Using the broadband point PSF of the segmented mirrors taken during a segment piston scan, the WLI can accurately detect small residual piston errors. WLI does not rely on extra optics and uses only the final imaging camera. With its high sensitivity to small segment piston error WLI can be used as a complementary phasing algorithm to the dispersed fringe sensor (DFS) for NGST. This paper will present the results from modeling and experiment on the NGST's Wavefront Control Testbed (WCT).
The NGST Wavefront Control Testbed (WCT) is a joint technology program managed by the Goddard Space Flight Center (GSFC) and the Jet Propulsion Laboratory (JPL) for the purpose of developing technologies relevant to the NGST optical system. The WCT provides a flexible testing environment that supports the development of wavefront sensing and control algorithms that may be used to align and control a segmented optical system. WCT is a modular system consisting of a Source Module (SM), Telescope Simulator Module (TSM) and an Aft-Optics (AO) bench. The SM incorporates multiple sources, neutral density filters and bandpass filters to provide a customized point source for the TSM. The telescope simulator module contains a flip-in mirror that selects between a small deformable mirror and three actively controlled spherical mirror segments. The TSM is capable of delivering a wide range of aberrated, unaberrated, continuous and segmented wavefronts to the AO optical bench for analysis. The AO bench consists of a series of reflective and transmissive optics that images the exit pupil of the TSM onto a 349 actuator deformable mirror that is used for wavefront correction. A Fast Steering Mirror (FSM) may be inserted into the system (AO bench) to investigate image stability and to compensate for systematic jitter when operated in a closed loop mode. We will describe the optical design and performance of the WCT hardware and discuss the impact of environmental factors on system performance.
A piston sensing and control algorithm for segmented mirror coarse phasing using a dispersed fringe sensor (DFS) has been developed for the Next Generation Space Telescope (NGST) wavefront sensing and control. The DFS can detect residual piston errors as large as the order of a depth-of-focus and can phase the segment mirrors with accuracy better than 0.1 microns, which is well within the capture range of fine phasing for NGST. A series of experiments have been carried out on the NGST's Wavefront Control Testbed (WCT) to validate the modeling results, evaluate the DFS performance, and systematically explore the factors that affect the DFS performance. This paper reports the testbed results for several critical issues of DFS performance, including DFS dynamic range, accuracy, fringe visibility, and the effects of segment mirror aberrations.
The STIS coronagraph performance is measured as a function of angle from the star, reaching 1×10-8 per resolution element compared to the total stellar flux at 2 arcsec with optimal PSF subtraction. Highly structured envelopes, disks, jets and
planetary clearings have been detected. Estimates of planet detectability with NGST show that Jupiter mass objects around the nearest stars should be detectable.
This paper describes the results of a few of the initial series of tests being conducted with the first configuration of the Next Generation Space Telescope Wavefront sensing and Control Testbed (WCT1). WCT1 is a 1:1, f/16.6 re-imaging system, incorporating two deformable mirrors located at pupil conjugate positions with 6 actuators/diameter (SM/DM) and 20 actuators/diameter (AO/DM). A CCD on a precision stage is used for obtaining defocused images providing phase diversity for wavefront determination using phase retrieval. In a typical experiment, wavefront error is injected into the optical path with the SM/DM and then corrected using the more densely actuated AO/DM. Wavefront analysis is provided via a phase retrieval algorithm, and control software is used to reshape the AO/DM and correct the wavefront. A summary of the results of some initial tests are presented.
Control algorithms developed for coarse phasing the segmented mirrors of the Next Generation Space Telescope (NGST) are being tested in realistic modeling and on the NGST wavefront control testbed, also known as DCATT. A dispersed fringe sensor (DFS) is used to detect piston errors between mirror segments during the initial coarse phasing. Both experiments and modeling have shown that the DFS provides an accurate measurement of piston errors over a range from just under a millimeter to well under a micron.
By segmenting and folding the primary mirror, quite large telescopes can be packed into the nose cone of a rocket. Deployed after launch, initial optical performance can be quite poor, due to deployment errors, thermal deformation, fabrication errors and other causes. We describe an automatic control system for capturing, aligning, phasing, and deforming the optics of such a telescope, going from initial cm-level wavefront errors to diffraction-limited observatory operations. This system was developed for the Next Generation Space Telescope and is being tested on the NGST Wavefront Control Testbed.
A telescope simulator was built as part of the Nexus wavefront control testbed, an NGST technology experiment at NASA's Goddard Space Flight Center. This testbed was designed to demonstrate complete control of a segmented telescope, from initial capture of light, through coarse alignment and phasing, to fine phasing and wavefront control. The existing telescope simulator allows testing of the fine phasing and wavefront control steps. A small deformable mirror in the simulator allows generation of an unobscured aberrated wavefront, for use in exploring the range of measurement and correction using the testbed's image-based wavefront sensor and larger deformable mirror. An alternate path under development for the simulator will create a segmented wavefront using three spherical mirrors; three-degree-of-freedom mounts under each mirror enable alignment and phasing experiments that will cover most of the operation sequence. Details of the hardware design and performance will be presented.
We are developing a two-dimensional array of microshutters which can be used as a high efficiency, high contrast field selection device for a multi-object spectrometer for the Next Generation Space Telescope (NGST). The device is a close- packed array of shutters, with a typical size of 100 microns square and area filling factor of up to 80%. Each shutter, made of single crystal silicon with an appropriate optical coating, pivots on a torsion flexure along one edge. Each of the shutters is individually selectable. An original double- shutter mechanism is employed for actuation. Since the device works in transmission, there is no loss of contrast due to diffraction from the edges of unactuated pixels. When working in reflection, the device can also be used as a micromirror array.
The Space Telescope Imaging Spectrograph (STIS), installed into the Hubble Space Telescope (HST) during the second servicing mission (SSM) in February 1197, has undergone the required servicing mission orbital verification (SMOV). The overall sensitivity of STIS is summarized for direct imagery in the visible with the charge coupled device (CCD), the near UV multi-anode microchannel-array (NUV MAMA) and the far UV MAMA (FUV MAMA) detectors and likewise for the spectroscopic modes. The FUV MAMA has exceedingly low background. The NUV MAMA has a higher, temperature-dependent background due to window phosphorescence. The principle gains of the CCD over WFPCs for limiting imaging sensitivity are: high quantum efficiency, wide bandpass, low dark current and low readout-noise. The CCD, like the WFPC2 CCDs, must ge annealed periodically to heat the hot pixels generated by radiation hits. Throughput of all modes has been stable at the 1 percent level or better except for the far UV, where sensitivity is dropping slowly across the order, but more rapidly below the Lyman alpha, and beyond 150 nm. This loss in sensitivity may be due to contamination similar to that which affected the first generation HST instruments. The thermal environment for STIS is warmer than specified in the HST Interface Control Document with the result that the back end of the STIS optical bench is not under positive thermal control. Temperature swings occur due to the spacecraft solar orientation and also due to power cycling of the MAMA low voltage power supplies that are turned off during orbits that encounter the South Atlantic Anomaly. Some motion of spectral and direct image formats occurs on the detector that is correlatable with changing aft bulkhead temperature and changes in external heatloads. The MAMA detectors are capable of time-tagging photon events within 125 microsecond resolution. The Crab Pulsar was used as a time standard and demonstrates the desired performance.
The space telescope imaging spectrograph (STIS) was designed as a versatile spectrograph capable of maintaining or exceeding the spectroscopic capabilities of both the Goddard High Resolution Spectrograph and the Faint Object Spectrograph (FOS) over the broad bandpass extending from the UV through the visible. STIS achieves performance gains over the aforementioned first generation Hubble Space Telescope instruments primarily through the use of large a real detectors in both the UV and visible regions of the spectrum. Simultaneous spatial and spectral coverage is provided through long slit or slitless spectroscopy. This paper will review the detector design and in-flight performance. Attention will be focussed on the key issue of S/N performance. Spectra obtained during the first few months of operation, illustrate that high signal-to-noise spectra can be obtained while exploiting STIS's multiplexing advantage. From analysis of a single spectrum of GD153, with counting statistics of approximately 165, a S/N of approximately 130 is achieved per spectral resolution element in the FUV. In the NUV a single spectrum of GRW + 70D5824, with counting statistics of approximately 200, yields a S/N of approximately 150 per spectral resolution element. An even higher S/N capability is illustrated through the use of the fixed pattern split slits in the medium resolution echelle modes where observations of BD28D42 yield a signal-to-noise of approximately 250 and approximately 350 per spectral resolution element in the FUV and NUV respectively.
The Space Telescope Imaging Spectrograph (STIS) is a second- generation instrument for the Hubble Space Telescope (HST), designed to cover the 115-1000 nm wavelength range in a versatile array of spectroscopic and imaging modes that take advantage of the angular resolution, unobstructed wavelength coverage, and dark sky offered by the HST. STIS was successfully installed into HST in 1997 February and has since completed a year of orbital checkout, capabilities that it brings to HST, illustrate those capabilities with examples drawn from the first year of STIS observing, and describe at a top level the on-orbit performance of the STIS hardware. We also point the reader to related papers that describe particular aspects of the STIS design, performance, or scientific usage in more detail.
The Space Telescope Imaging Spectrograph (STIS) operates from the UV to near IR providing a general purpose, imaging spectroscopic capability. An internal, two mirror relay system corrects the spherical aberration and astigmatism present at the STIS field position. Low and medium resolution imaging spectroscopy is possible throughout the spectral range and over the 25 arcsecond UV and 52 arcsecond visible fields. High resolution echelle spectroscopy capability is also provided in the UV. Target acquisition is accomplished using the STIS cameras, either UV or visible; these cameras may also be used to provide broad band imaging over the complete spectral range or with the small selection of available bandpass filters. A wide selection of slits and apertures permit various combinations of spectral resolution and field size in all modes. On board calibration lamps provide wavelength calibration and flat fielding capability. We report here on the optical performance of STIS as determined during orbital verification.
The STIS instrument was installed into HST in February 1997 during the Servicing Mission 2. It has almost completed checkout and is beginning its science program, and is working well. Several scientific demonstration observations were taken to illustrate some of the range of scientific uses and modes of observation of STIS.
The second servicing mission for the Hubble Space Telescope (HST), scheduled for early 1997, will be the first change in the spectroscopic capabilities of HST since its initial deployment. The Space Telescope Imaging Spectrograph (STIS) is a multipurpose instrument covering the far ultraviolet (FUV) through near infrared spectral range. It acquires spectra at several spectral resolutions, which facilitates observations at many distances and brightnesses. STIS will replace both of the first generation spectrographs, the Goddard High Resolution Spectrograph and the Faint Object Spectrograph. This will allow the addition of a Near- Infrared Camera. STIS required the development and testing of many high quality diffraction gratings, including several very difficult echelles for the FUV. The methods and results of this grating development program are presented. The results serve as a snapshot of industry capabilities for producing high quality spaceborne diffraction gratings.
For detectors using microchannel plates (MCPs), the nonuniform response introduced by the finite size of the MCP pores has a significant effect when the size of a resolution element is comparable to the spacing between the pores (approximately 10 - 15 micrometers ). For the Far Ultraviolet Spectroscopic Explorer (FUSE) spectrograph, which will employ a delay line detector, the instrument plate scale, nominal slit width (1 arcsecond), and well-corrected optical design combine to produce slit-limited images 25 micrometers in width with resolution elements 32 micrometers wide, and a nominal resolution of (lambda) /(Delta) (lambda) equals 30,000. At these scales, the MCPs will sparsely sample spectral line images, resulting in significant pixellation effects. We have constructed a computer model of a microchannel plate detector to simulate these effects and evaluate the performance that can be expected from the FUSE detector. These simulations have been compared to actual images obtained with a laboratory version of a delay line detector. Slit patterns imaged onto the detector were chosen to simulate the resolution expected from the FUSE spectrograph in order to provide an estimate of the expected resolving power and test the effects of several detector parameters on resolution. Details of the model are described, and a comparison of the results with laboratory data is made. The implications for FUSE are also discussed.
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.