New mission concepts that are under consideration by NASA call for the design and implementation of Far Ultraviolet (FUV) polarizer technologies that have not been developed yet. A team that includes members from the NASA Goddard Space Flight Center (GSFC), Arizona State University (ASU), and Woodruff Consulting, worked on the design and development of a polarizer design that produce very high extinction ratios in the FUV spectral range (100-200 nm). This polarizer consists of reflecting light through a series of mirrors from a combination of two silicon carbide (SiC) and two lithium fluoride (LiF) crystals positioned at angles of incidence (relative to surface normal) close to the average LiF Brewster’s angle in the FUV. The output is a highly linearly polarized beam. This polarizer concept was fabricated and tested in the existing McPherson 225 Vacuum Ultraviolet (VUV) spectrometer located in the Optics Branch at NASAGSFC. Initial testing using a MgF2 crystal at the Brewster’s angle as an analyzer has shown that this design can produce state-of-the-art extinction ratios at the Hydrogen Lyman-Alpha (Ly-α) wavelength of 121.6 nm, and that the measured extinction ratio of the two crossed polarizers, ≈114, is mostly limited by the MgF2 analyzer. A polarizer with such a performance at this wavelength has never been reported and it signifies a breakthrough in FUV polarization technology. The levels of effectiveness paired with the polarizer’s compact design allows for a new polarizer capability that would one day be implemented in a future FUV spectropolarimetry space mission.
The solar transition region ultraviolet explorer (STRUVE) is a proposed CubeSat mission to study the magnetic field in the solar atmosphere from the photosphere up to the top of the chromosphere. The STRUVE instrument is a full-Stokes spectro-polarimeter and observes a region of the near-UV that contains the well-known Mg II h- and k-lines as well as a number of Fe I- and Fe II-lines that sample many heights in the atmosphere. In order to accurately determine the magnetic field strength and orientation, STRUVE has sub-arcsecond yaw and pitch pointing stability requirements to suppress crosstalk between Stokes parameters. One of our concept study priorities is addressing the fine pointing requirements to demonstrate mission feasibility. This paper provides an overview of the STRUVE CubeSat and related background, the main sources of jitter and our ADCS solutions. We present several studies that provide rationale for pointing system design choices and review tools that have been developed to demonstrate system capabilities.
The Polstar NASA medium explorer (MIDEX) design configuration and implementation is strongly driven by the requirement to measure the state of polarization of stellar objects using a space-based sensor. Constraints include, but are not limited to, symmetry of geometry and coatings of the collecting aperture, angle of incidence at optical surfaces, coating uniformity, line of sight jitter and drift, orbit properties, thermal stability, and ground calibration. The Polstar MIDEX will observe scientifically interesting stars. Polstar will simultaneously measure all four Stokes parameters (I, Q, U, V) to high accuracy and precision (~0.001%) of the Stokes vector at high spectral resolving power. The 600-mm diameter aperture telescope images a selected star at the entrance slit of a spectrometer. Polstar offers two spectral channels within one spectrometer: a Far UV 122 nm to 200 nm Channel 1 with R~30K spectral resolving power and a low spectral resolution in Channel 2 channel covering 180 nm to 320 nm with R ~ 120 to 4K and spectroscopy over 115 nm to ~1,000nm. Channel 1 uses a cross-dispersed echelle spectrometer design. Channel 2 achieves its spectral dispersion with a MgF2 prism disperser. The two channels share a common array detector. The spectrometer includes rotating MgF2 retarders and a fixed MgF2 Wollaston prism analyzer to implement a dual beam polarization sensing function. Two orthogonal polarization states are imaged onto the array detector as interleaved echellograms (Channel 1) and as parallel spectra (Channel 2). This paper presents the design resulting from these design constraints and describes the approaches to calibrate the design pre-flight and during flight.
We are developing the design for the Lyman-Ultraviolet (LUV) Imaging Spectrograph, LUVIS to propose for a small explorer (SMEX) mission. LUVIS will provide true long slit (six arc minute) imaging spectroscopic capability with large spectral resolving power, R. Minimizing the number of optical components to the required minimum of three enables large spectral throughput. The design uses a two-mirror Cassegrain Ritchey-Chretien Optical Telescope assembly (OTA), a single optic Rowland-like spectrometer, and a windowless 50 x 127 mm curved microchannel plate (MCP). The design is optimized over the 102 to 140 nm spectral range providing spectral imaging at R ~ 20K in a single exposure. Lyman-β enhanced Al + LiF mirror and grating coatings with the LiF protected with an atomic layer deposition (ALD) fluoride encapsulating overcoat provide high throughput over that spectral range. Line-of-sight (LOS) jitter control utilizes time-tag photon arrival to compensate field position jitter by re-registering pixel location in post-processing as well as tip/tilt active control of the secondary mirror of the OTA. This paper will describe the design as well as some of the key design trades that defined the design.
The Polstar Mission uses time domain FUV and NUV spectropolarimetric observations to provide insight into how our galaxy became able to support a solar system like ours. Polstar will study the evolution of massive stars, including the inter-stellar dust and gas that they interact with and the dynamics of protoplanetary disks and lower resolution near UV (180nm – 320 nm) to study interstellar reddening mechanism. Polstar will simultaneously measure at high spectral resolving power all four Stokes parameters (I, Q, U, V)T to high accuracy (0.001) with a precision better than 0.0001 using an instrument comprising a modulator with rotating MgF2 retarders and a fixed MgF2 Wollaston prism analyzer that concurrently measures the two orthogonal polarizations of the retarder modulated signal at six optimized rotational angles on a common detector. The output of the Wollaston prism either directly enters an echelle spectrograph, which provides spectral resolution of ~30K with a wavelength range from 122 nm to 200 nm, or is reflected to a prism spectrograph, which provides spectral resolution ranging from 140– 4000 with a wavelength range from 180 nm to 320 nm. In this paper we outline the instrument calibration approach to obtain the Mueller matrices over the full wavelength range that permit us to determine the Stokes parameters, and to spectrally calibrate the instrument. We also describe the ground support equipment for calibration.
The Lyman-UV imaging spectrograph (LUVIS) is a NASA SMEX mission concept. Here, we describe the basic scientific requirements of LUVIS and instrumental requirements derived from the scientific requirements. Other papers in this conference by Woodruff et al. and Kendrick et al. describe the LUVIS instrument in detail.
The solar transition region ultraviolet explorer (STRUVE) is a proposed CubeSat mission with a slit-scanning, full-Stokes spectropolarimeter that will observe the Sun with a spectral range of about 259 to 281 nm. STRUVE addresses two main high-level science objectives: 1) understand the magneto-fluid conditions at the base of the corona and the build-up and release of magnetic energy; and 2) understand how the magnetic and plasma properties at the base of the solar corona vary between open and closed magnetic structures. This paper aims to illustrate the flow down of requirements from the mission science objectives to design requirements while also giving an overview of the design developed from the concept study. The derived requirements from the science objectives are the primary functions STRUVE will need to perform to capture the needed data for the mission. The overview of the mission design will delve into the mission operations and give an overview of the STRUVE instrument and spacecraft. Links between the requirements and mission design are made, pointing out how critical requirements are being met. Throughout the paper, trade studies are presented showing the rationale behind many of the critical design choices made in developing STRUVE for the concept study
Polstar combines, for the first time, the complementary benefits of spectroscopy and polarimetry to probe the complex interface between massive stars and the interstellar medium. Furthermore, it leverages an innovative combination of effective area and time coverage, to reach the diversity of targets necessary to transform our understanding of the ecology of star and planet creation. Detailed knowledge of these bright, yet distant objects, is crucial for understanding the transformation of our galaxy, from the barren landscape of the early Big Bang, into the chemically enriched environment that produced the solar system we call home. Polstar will map stellar wind and magnetospheric structures by uniting time domain, polarimetry and spectroscopy capability in the near- and far-UV (NUV and FUV), which are densely populated with high-opacity resonance lines encoding a rich array of diagnostic information. UV spectropolarimetry is equally important for probing interstellar dust and protoplanetary disks. The instrument combines advances in high reflectivity UV coatings and delta-doped CCDs with high quantum efficiencies to provide dedicated FUV spectropolarimetry for the first time in 25 years. The FUV channel (Ch1), covers 122-200nm at resolution R>30k, while the NUV channel (Ch2) covers 122-320nm at R~140-4,000. The instrumental polarization stability is built to provide signal-to-noise ratios (SNR) for UV polarimetry precision of 1x10-3 per exposure per resolution element (resel). Precision can be further improved with spectral binning and/or stacking multiple exposures. Polstar spectral resolution in Ch1 is >30x better than WUPPE, with 10x better effective area, while reaching shorter wavelength than WUPPE to access strong lines of species like NIV and SiIV. The 3-year mission of Polstar is 100x longer than WUPPE with orders of magnitude gains in stellar and interstellar observations.
The Lyman UV imaging spectrograph (LUVIS) accomplishes priority UV science contained in the budget of a SMEXclass mission. LUVIS consists of a 0.5-m f/24 Cassegrain optical telescope assembly feeding a UV/ far-UV spectrometer. LUVIS has a long 6 arcmin slit enabling spectral imaging and is optimized for 102-140 nm with a resolving power of 20,000 on a micro-channel plate detector with a CsI photocathode. The light gathering power is designed to reach galaxies with near-UV fluxes as low as 10-14 erg/s/cm2 /Å (and lower with long time exposures). The design approach encompasses a simple but elegant optical design, minimum number of reflective surfaces, limited mechanisms, and an orbit minimizing fuel requirements while offering operational advantages. All components are already at a high technology readiness level further reducing technical and cost risk to meet a SMEX budget with healthy cost reserves.
The Polstar Mission seeks to study the evolution of massive stars including their effect on the interstellar medium and their behavior in binary systems using a 60 cm telescope with a UV Spectropolarimeter within MIDEX mission constraints on cost cap, throughput, coating requirements, and system-level dimensional stability. The mission is in a high-earth orbit and must ensure precise and repeatable polarimetric observations. Design-to-cost paradigms are exercised throughout all design phases and heritage approaches to structure and mirrors are evoked. In terms of classical error budgets, designing for diffraction-limited performance at 1.2 μm is sufficient, however, there are special design concerns at these wavelengths which require maximizing throughput of photons. Special coatings and minimum reflections are mandatory with meticulous attention to cleanliness throughout the entire mission life cycle. Decontamination heaters must be employed shortly after launch, prior to opening the door, and periodically throughout the mission lifetime. Additionally, spectropolarimetry requirements impose constraints on symmetry and control of phase and amplitude. The secondary mirror must have adjustment capability in three degrees of freedom (tip, tilt, and focus) to address drifts from thermal perturbations, aging, and possibly even spacecraft jitter. We present in-process design approach and analyses to meet the challenges of ultraviolet wavelengths and polarization stability..
From studying the fossil records of stars to exploring the circumgalactic medium, UV astronomy is a field rife with scientific opportunity. CETUS is a proposed next-generation UV space telescope equipped with a suite of instruments tailored to the study of UV phenomena in our galaxy. To achieve diffraction-limited imaging and spectroscopy performance at short wavelengths, a high-performance and resolution optical design is necessary. We describe the telescope design options including a trade study between a traditional on-axis TMA and freeform off-axis TMA solution considering their alignment sensitivity and tolerances. Different secondary support structures are explored for the on-axis design to analyze the irradiance distribution of the point-spread function (PSF) due to the pupil obscuration and how it influences the simulated starfield at the telescope focal planes. With rigorous analysis we aim to enable the next spaceborne observatory for UV astronomy.
The Polstar mission will provide for a space-borne 60cm telescope operating at UV wavelengths with spectropolarimetric capability capturing all four Stokes parameters (intensity, two linear polarization components, and circular polarization). Polstar’s capabilities are designed to meet its goal of determining how circumstellar gas flows alter massive stars' evolution, and finding the consequences for the stellar remnant population and the stirring and enrichment of the interstellar medium, by addressing four key science objectives. In addition, Polstar will determine drivers for the alignment of the smallest interstellar grains, and probe the dust, magnetic fields, and environments in the hot diffuse interstellar medium, including for the first time a direct measurement of the polarized and energized properties of intergalactic dust. Polstar will also characterize processes that lead to the assembly of exoplanetary systems and that affect exoplanetary atmospheres and habitability. Science driven design requirements include: access to ultraviolet bands: where hot massive stars are brightest and circumstellar opacity is highest; high spectral resolution: accessing diagnostics of circumstellar gas flows and stellar composition in the far-UV at 122-200nm, including the NV, SiIV, and CIV resonance doublets and other transitions such as NIV, AlIII, HeII, and CIII; polarimetry: accessing diagnostics of circumstellar magnetic field shape and strength when combined with high FUV spectral resolution and diagnostics of stellar rotation and distribution of circumstellar gas when combined with low near-UV spectral resolution; sufficient signal-to-noise ratios: ~103 for spectropolarimetric precisions of 0.1% per exposure; ~102 for detailed spectroscopic studies; ~10 for exploring dimmer sources; and cadence: ranging from 1-10 minutes for most wind variability studies, to hours for sampling rotational phase, to days or weeks for sampling orbital phase. The ISM and exoplanet science program will be enabled by these capabilities driven by the massive star science.
KEYWORDS: Ultraviolet radiation, Ultraviolet telescopes, Telescopes, Astrophysics, Large telescopes, Space telescopes, James Webb Space Telescope, Hubble Space Telescope, Space operations
We report on the status of CETUS, an all-UV, Probe-class mission concept to be evaluated by the Astro2020 Steering Panel. This report expands and updates the scientific uses of CETUS and CETUS technology as described earlier by Kendrick et al. (2019). The major updates derive form technological advances that promise to make CETUS a scientifically more powerful and long-lived space observatory than originally proposed. A long, useful lifetime will be needed to fulfill the future needs of the astronomical and planetary-science community.
The Cosmic Evolution Through UV Surveys (CETUS) concept has three UV instruments to achieve its science goals that work in the near ultraviolet (NUV) and far ultraviolet (FUV). The NUV multi-object spectrograph (MOS) and the NUV/FUV Camera operate simultaneously with their separate field of views. The key enabling technologies will be discussed including the micro-shutter array, detectors, and optical coatings. The NUV MOS can target up to 100 objects at a time which will allow over 100,000 galaxies to be observed during the mission lifetime. The UV Camera has the capability to image from the FUV to the NUV at the same time the MOS is operating at 180-350 nm. The UV Camera has a selection of bandpass filters, longpass filters, and two separate detectors to optimize observing in either the FUV or the NUV utilizing a sealed CsI solar blind micro-channel plate and a 4Kx4K CCD respectively. Both instruments have a tip/tilt/focus mechanism on one of their optics allowing independent focus correction and dithering of the image at the focal plane.
In support of a spaceborne astrophysics instrument design, we have studied high UV filter efficiency and strong transmission blocking out to the end of Si response at 1100nm. For filters at wavelengths 297.5nm/338.5nm/379.5nm, these attributes are achieved with the combination of hard sputtered dielectric coatings on colored glass substrates. The filterglass substrates can be used to suppress ghost images caused by reflection at the exit face which is a common problem of all interference filter designs. Known disadvantages of filterglasses like solarization or autofluorescence are discussed and possible ways to mitigate are discussed. At two shorter wavelengths, 215.5nm and 256.5nm, metaldielectric Fabry-Perot stacks are applied on fused silica. Those traditional designs are advantageous due to their efficient blocking up to the mid IR range and economic low number of layers. We discuss the different design possibilities of metal-dielectric filters and ways to improve the steepness of the slopes. Resulting spectra are expressed.
As part of a study funded by NASA headquarters, we are developing a probe-class mission concept called the Cosmic Evolution through UV Spectroscopy (CETUS). CETUS includes a 1.5-m aperture diameter telescope with a large field of view (FOV). CETUS includes three scientific instruments: a far ultraviolet (FUV) and near ultraviolet (NUV) imaging camera (CAM); a NUV multiobject spectrograph (MOS); and a dual-channel point/slit spectrograph (PSS) in the Lyman ultraviolet (LUV), FUV, and NUV spectral regions. The large FOV three-mirror anastigmatic (TMA) optical telescope assembly (OTA) simultaneously feeds the three separate scientific instruments. That is, the instruments view separate portions of the TMA image plane, enabling parallel operation by the three instruments. The field viewed by the MOS, whose design is based on an Offner-type spectrographic configuration to provide wide FOV correction, is actively configured to select and isolate numerous field sources using a next-generation micro-shutter array. The two-channel CAM design is also based on an Offner-like configuration. The PSS performs high spectral resolution spectroscopy on unresolved objects over the NUV region with spectral resolving power, R ∼ 40,000, in an echelle mode. The PSS also performs long-slit imaging spectroscopy at R ∼ 20,000 in the LUV and FUV spectral regions with two aberration-corrected, blazed, holographic gratings used in a Rowland-like configuration. The optical system also includes two fine guidance sensors, and wavefront sensors that sample numerous locations over the full OTA FOV. In-flight wavelength calibration is performed by a wavelength calibration system, and flat-fielding is also performed, both using in-flight calibration sources. We describe the current optical design of CETUS and the major trade studies leading to the design.
Several classes of planetary science observations require high spatial resolution in UV and visible wavelengths. Key examples include (a) the detection of satellites and characterization of their orbits, (b) the discovery of faint and small objects among the NEO, asteroid, Kuiper belt or Sedna-like populations and (c) cloud or trace gas observations in planetary atmospheres. Hubble Space Telescope (HST) observations have been very productive in these areas: consider the recent discovery of Makemake's satellite (Parker et al., 2016), the discovery of 2014 MU69 (now the flyby target of the New Horizons spacecraft) or the OPAL (Outer Planet Atmospheres Legacy) program.
Like HST, large-aperture ground-based telescopes with adaptive optics can also achieve spatial resolutions of 50 mas, but normally at wavelengths longer than ~1 μm. Projects like MagAO-2K are working on improving image quality at visible wavelengths, but while the core PSF (Point Spread Function) width might be narrow (projected to be 15 mas at the Magellan telescope), the Strehl ratio drops steeply with wavelength (Males et al., 2016). Not all science goals suffer equally from low Strehl ratios, however: cloud tracking on Venus is more tolerant of a low Strehl ratio than searching for a close satellite of Makemake.
A telescope on a NASA super-pressure balloon would float above 99.3% of the atmosphere, where the inner Fried parameter is thought to be two meters or more. While atmospheric turbulence is not expected to impact image quality, there are other sources of wavefront error (WFE), such as mirror figuring, misalignment of the OTA (Optical Telescope Assembly) or asymmetric heating from the Sun or Earth. We reference recent work that estimates balloon telescope WFEs from different sources to generate a suite of plausible PSFs. We apply these PSFs to the UV and visible wavelength science cases outlined in the GHAPS/SIDT report (Gondola for High Altitude Planetary Science/Science Instrument Definition Team). We quantify the impact that WFE has on achieving the planetary observations outlined in the SIDT report.
The environment of a balloon based telescope puts opto-mechanical stability demands that wavefront sensing and focus control are important features to consider. The GHAPS telescope is designed to correct for rigid body motion of the secondary mirror based upon wavefront sensing from reference stars. In order to support the concept of operations of this approach, the precision of wavefront sensing with candidate reference stars needs to be addressed. Precision is expected to degrade with reduction in irradiance. To confirm this, a study was conducted to determine the relationship between broadband and narrow spectral irradiance and wavefront measurement precision. The results of the study demonstrate that a precision of 5 nm RMS can be achieved with a 20 x 20 sampling of the wavefront with an irradiance of a visual magnitude 5 star on 1 meter aperture with an exposure of 30 msec.
Balloon based telescopes represent an opportunity to observe science in an environment with almost no atmospheric effects. However, balloon based platforms include a wide range of thermal environments as well as pointing a lightweight telescope over a large elevation range. The Gondola for High Altitude Planetary Science (GHAPS) was designed to provide nearly diffraction limited performance observations over the visible and infrared spectrum with a 1- meter aperture. To achieve such performance, detailed Structural Thermal Optical Performance (STOP) was used to predict telescope performance. Software was built to automate the process of analysis, enabling thermal, structural and optical analyses to be executed quickly with less effort. The end result was the capability to analyze both generic operating conditions and Design Reference Mission conditions, producing predictions that could be used to evaluate the quality of science return.
The importance of high performance interference bandpass filters in the UV is growing recently. For the CETUS project a set of bandpass filters with a clear aperture of 70 mm is required centered at the wavelengths 215.5 nm / 256.5 nm / 297.5 nm / 338.5 nm / 379.5 nm with a FWHM of 41 nm and blocked as good as possible up to 1100 nm. We present a design study based on all-dielectric hard sputtered coatings on colorglass substrates for the wavelengths 297.5 nm / 338.5 nm / 379.5 nm. The colorglass substrates where chosen to suppress ghost images by reflection on the exit face and to improve the blocking in the required range. For the wavelengths 215.5 nm and 256.5 nm a conventionally evaporated design of metal-dielectric Fabry-Perot stacks was chosen on fused silica substrates. We comment on how system requirements are leading to filter specifications and show theoretical spectra of the chosen filter designs.
The Gondola for High-Altitude Planetary Science (GHAPS) project is a balloon-borne astronomical observatory designed operate in the UV, Visible, and near-mid IR spectral region. The GHAPS Optical Telescope Assembly (OTA) is designed around a one meter aperture narrow field-of-view telescope with near-diffractionlimited performance. GHAPS will utilize Wallops Arc-Second Pointing System (WASP) for pointing the OTA with an accuracy of 1 arc second or better. WASP relies heavily on a self-contained star tracker assembly to determine the OTA line of sight. Preliminary structural analysis indicates that potential misalignments could be present between the OTA line of sight and the star tracker FOV center during the expected flight conditions that could compromise GHAPS pointing accuracy. In response the GHAPS project undertook a trade study to resolve the following issues: (1) estimate the worst case long-term (or bias) pointing misalignments for the GHAPS opto-mechanical configuration, (2) examine the need for additional hardware to correct pointing errors, and (3) determine the best hardware and software implementation to do so. Quantitative comparisons of performance and qualitative estimates of other factors such as mass, volume, power consumption, and cost are combined into an overall assessment of potential solutions. Results are discussed and a recommended implementation is given that is optimized to best achieve pointing performance goals, while minimizing impact to the design, cost, and resources of the GHAPS project.
The Cosmic Evolution Through UV Spectroscopy (CETUS) concept1-3 enables parallel observations by the UV multiobject spectrometer (MOS) and near-UV/far-UV camera which operate simultaneously but independently with their separate field of views. The near-UV MOS can target up to 100 objects at a time without confusion with nearby sources or background zodiacal light. This multiplexing will allow over 100,000 galaxies to be observed over a typical mission lifetime. The MOS includes a next-generation micro-shutter array (NGMSA), an efficient aspheric Offner-like spectrometer design with a convex grating, and nanotube light traps for suppressing unwanted wavelengths. The NUV/FUV Camera has the capability to image in a range of sub-bands from 115-400 nm at the same time the MOS is operating at 180-350 nm. The UV camera has a similar Offner-like relay, selectable filters, and two separate detectors to optimize observing in either the far-UV (115-175 nm) or the near-UV (180-400 nm) utilizing a CsI Micro-Channel Plate detector (MCP) and a CCD respectively.
The ultraviolet multi-object spectrograph (MOS) for the Cosmic Evolution Through UV Spectroscopy (CETUS) concept1,2 is a slit-based instrument allowing multiple simultaneous observations over a wide field of view. It utilizes a next-generation micro-shutter array, an efficient aspheric Offner spectrometer design with a convex grating, and carbon nanotube light traps for suppressing unwanted wavelengths. The optical coatings are also designed to optimize the UV throughput while minimizing out-of-band signal at the detector. The UV MOS will be able to target up to 100 objects at a time without the issues of confusion with nearby sources or unwanted background like zodiacal stray light. With this multiplexing, the scientific yield of both Probe and Great Observatories will be greatly enhanced.
We report on the early phases of a NASA-sponsored study of CETUS (Cosmic Evolution Through Ultraviolet Spectroscopy), a Probe-class mission concept. By definition, the full lifecycle cost of a Probe mission is greater than $400M (i.e. Explorer missions) and less than $1.00B (“Flagship” missions). The animating idea behind our study is that CETUS can help answer fundamental questions about galaxy evolution by carrying out a massive UV imaging and spectroscopic survey of galaxies and combining its findings with data obtained by other survey telescopes of the 2020’s. The CETUS mission concept comprises a 1.5-m wide-field telescope and three scientific instruments: a near-UV multi-object slit spectrograph with a micro-shutter array as the slit device; a near-UV and far-UV camera with angular resolution of 0.42” (near-UV) or 0.55” (far-UV); and a near-UV or far-UV single-object spectrograph aimed at providing access to the UV after Hubble is gone. We describe the scientific rationale for CETUS and the telescope and instruments in their early design phase.
We are developing a NASA Headquarters selected Probe-class mission concept called the Cosmic Evolution Through UV Spectroscopy (CETUS) mission, which includes a 1.5-m aperture diameter large field-of-view (FOV) telescope optimized for UV imaging, multi-object spectroscopy, and point-source spectroscopy. The optical system includes a Three Mirror Anastigmatic (TMA) telescope that simultaneously feeds three separate scientific instruments: the near-UV (NUV) Multi-Object Spectrograph (MOS) with a next-generation Micro-Shutter Array (MSA); the two-channel camera covering the far-UV (FUV) and NUV spectrum; and the point-source spectrograph covering the FUV and NUV region with selectable R~ 40,000 echelle modes and R~ 2,000 first order modes. The optical system includes fine guidance sensors, wavefront sensing, and spectral and flat-field in-flight calibration sources. This paper will describe the current optical design of CETUS.
With sub-microarcsecond astrometry, exoplanets can be identified and their masses measured. Coronagraphic imaging of
these exoplanets is required to study their atmospheres and surfaces in sufficient detail to identify possible signs of
biological activity. We show how both measurements can be simultaneously acquired with a single telescope in which
the central field is directed to a coronagraph instrument providing high contrast images, while the surrounding field is
imaged with a wide field camera in which numerous faint background stars are used as an astrometric reference. To
calibrate astrometric distortions due to optics and focal plane detector array imperfections and variations, we propose to
place small dark spots on the telescope primary mirror. The spots, arranged in a regular grid containing no low spatial
frequencies, do not affect the coronagraph performance. In the wide field image, they create diffraction spikes
originating from the central bright star, which are affected by changes in intrumental distortions in exactly the same way
as the background stars used for reference, thus allowing calibration of instrumental errors to micro-arcsecond level. We
show that combining simultaneous astrometric and coronagraphic measurements allows reliable detection and
characterization of exoplanets. Recent laboratory tests performed at the University of Arizona and NASA Ames validate
the concept, demonstrating both the ability to accurately calibrate astrometric distortions, and compatibility with high
contrast imaging systems.
A concept for high precision astrometry with a conventional wide field telescope is presented, enabling a space
telescope to perform simultaneously coronagraphic imaging of exoplanets, astrometric measurement of their
orbits and masses, and deep wide field imaging for a wide range of astrophysical investigations. Our concept uses
a diffractive telescope pupil (primary mirror), obtained by placing a regular grid of small sub millimeter spots
on the primary mirror coating. When the telescope is pointed at a bright star, the wide field image contains
both a large number of background stars used for astrometric referencing, and faint diffraction spikes created
by the grid of dots on the primary mirror. The diffraction spikes encode instrumental astrometric distortions
due to optics or the detector, allowing precise measurement of the central star against a large number of faint
background stars. With up to a few percent of the primary mirror area covered by the dots, the fraction of the
central starlight located in the diffraction spikes is kept sufficiently small to allow full sensitivity deep imaging
over the telescope's field of view. Since the dots are regularly spaced, they do not diffract light at small angular
separations, and therefore allow full coronagraphic imaging capability. We show that combining simultaneous
astrometric and coronagraphic measurements allows improved detection and characterization of exoplanets by
constraining the planet(s) characteristics with both measurements. Our preliminary astrometric accuracy error
budget shows that sub-micro arcsecond astrometry can be achieved with a 1.4 m diameter telescope, and that
astrometric accuracy improves rapidly with telescope diameter.
The James Webb Space Telescope (JWST) is a general astrophysics mission which consists of a 6.6m diameter,
segmented, deployable telescope for cryogenic IR space astronomy (~35K). The JWST Observatory architecture
includes the Optical Telescope Element and the Integrated Science Instrument Module (ISIM) element that contains four
science instruments (SI) including a Guider.
The alignment philosophy of ISIM is such that the cryogenic changes in the alignment of the SI interfaces are captured in
the ISIM alignment error budget. The SIs are aligned to the structure's coordinate system under ambient, clean room
conditions using laser tracker and theodolite metrology. The ISIM structure is thermally cycled and temperature-induced
structural changes are concurrently measured with a photogrammetry metrology system to ensure they are within
requirements.
We compare the ISIM photogrammetry system performance to the ISIM metrology requirements and describe the
cryogenic data acquired to verify photogrammetry system level requirements, including measurement uncertainty. The
ISIM photogrammetry system is the baseline concept for future tests involving the Optical Telescope Element (OTE) and
Observatory level testing at Johnson Space Flight Center.
The Star Formation Camera (SFC) is a wide-field (~19'×~15', >280 arcmin2), high-resolution (18 mas pixels) UV/optical
dichroic camera designed for the Theia 4-m space-borne space telescope concept. SFC will deliver diffraction-limited
images at λ > 300 nm in both a blue (190-517nm) and a red (517-1075nm) channel simultaneously. The goal is to
conduct a comprehensive and systematic study of the astrophysical processes and environments relevant for the births
and life cycles of stars and their planetary systems, and to investigate the range of environments, feedback mechanisms,
and other factors that most affect the outcome of star and planet formation.
This paper presents the optical design of the Dilute Aperture Visible Nulling Coronagraph Imaging (DAViNCI).
DAViNCI's dilute aperture approach to the TPF-C extra-solar earth-like detection mission reduces cost and technical
risk compared to other filled aperture approaches. DAViNCI has been studied in an ASMCS (Astrophysics Strategic
Mission Concept Study) and is included within the ASTRO2010 Decadal review [1]. The DAViNCI team is led by
Michael Shao (PI) of JPL.
Three of the recently completed NASA Astrophysics Strategic Mission Concept (ASMC) studies addressed the
feasibility of using a Visible Nulling Coronagraph (VNC) as the prime instrument for exoplanet science. The VNC
approach is one of the few approaches that works with filled, segmented and sparse or diluted aperture telescope systems
and thus spans the space of potential ASMC exoplanet missions. NASA/Goddard Space Flight Center (GSFC) has a
well-established effort to develop VNC technologies and has developed an incremental sequence of VNC testbeds to
advance the this approach and the technologies associated with it. Herein we report on the continued development of the
vacuum Visible Nulling Coronagraph testbed (VNT). The VNT is an ultra-stable vibration isolated testbed that operates
under high bandwidth closed-loop control within a vacuum chamber. It will be used to achieve an incremental sequence
of three visible light nulling milestones of sequentially higher contrasts of 108, 109 and 1010 at an inner working angle of
2*λ/D and ultimately culminate in spectrally broadband (>20%) high contrast imaging. Each of the milestones, one per
year, is traceable to one or more of the ASMC studies. The VNT uses a modified Mach-Zehnder nulling interferometer,
modified with a modified "W" configuration to accommodate a hex-packed MEMS based deformable mirror, a coherent
fiber bundle and achromatic phase shifters. Discussed will be the optical configuration laboratory results, critical
technologies and the null sensing and control approach.
High precision astrometry of nearby bright stars is theoretically (in the photon noise limit) possible with a space coronagraph using a wide field diffraction limited camera imaging an annulus of background stars around the central coronagraphic field. With the sub-micro arcsecond accuracy theoretically achievable on a 1.4-m telescope, the mass of all planets that can be imaged by the coronagraph would be estimated. Simultaneous imaging and astrometric measurements would reduce the number of astrometric measurements necessary for mass determination, and reduce confusion between multiple planets and possible exozodiacal clouds in the coronagraphic image. While scientifically attractive, this measurement is technically very challenging, and must overcome astrometric distortions, which, in conventional telescopes, are several orders of magnitude above the photon noise limit. In this paper, we propose a new approach to calibrating astrometric distortions in the wide field imaging camera. The astrometric measurement is performed by simultaneously imaging background stars and diffraction spikes from the much brighter coronagraphic target on the same focal plane array. The diffraction spikes are generated by a series of small dark spots on the primary mirror to reduce sensitivity to optical and mechanical distortions. Small scale distortions and detector errors are averaged down to sub-micro arcsecond by rolling the telescope around the line of sight. A preliminary error budget is shown and discussed to identify major sources of error for a 1.4-m telescope imaging a 0.25 squaredeg field of view at the galactic pole.
Herein we report on a preliminary study to assess the use of the Hubble Space Telescope (HST) for the direct detection
and spectroscopic characterization of exoplanets and debris disks - an application for which HST was not originally
designed. Coronagraphic advances may enable the design of a science instrument that could achieve limiting contrasts
~109 beyond 275 milli-arcseconds (4 λ/D at 800 nm) inner working angle, thereby enabling detection and
characterization of several known jovian planets and imaging of debris disks. Advantages of using HST are that it
already exists in orbit, it's primary mirror is thermally stable and it is the most characterized space telescope yet flown.
However there is drift of the HST telescope, likely due to thermal effects crossing the terminator. The drift, however, is
well characterized and consists of a larger deterministic components and a smaller stochastic component. It is the effect
of this drift versus the sensing and control bandwidth of the instrument that would likely limit HST coronagraphic
performance. Herein we discuss the science case, quantify the limiting factors and assess the feasibility of using HST for
exoplanet discovery using a hypothetical new instrument.
The Joint Dark Energy Mission (JDEM)1,2 is a proposed dark energy space mission that will measure the
expansion history of the universe and the growth of its large scale structure. It is intended to provide tight
constraints on the equation of state of the universe and test the validity of general relativity. Three
complementary observational analyses will be employed: Baryon Acoustic Oscillations, Type 1a Supernovae
and Gravitational Weak Lensing. An observatory designed for efficient accommodation of these techniques
combines wide-field, diffraction-limited observations, ultra-stable point spread function, and spectroscopy.
In this paper we discuss optical configurations capable of simultaneous wide-field imaging and spectroscopy,
using either afocal or focal telescope configurations. Spectroscopy may be performed by an integral field unit
(IFU), grism or prism spectrometer. We present a flowdown of weak lensing image stability requirements
(the most demanding technique optically) to telescope thermo-mechanical stability limits, based on variations
in the optical transfer function of combinations of Zernike modes, and the sensitivity of these mode
combinations to thermo-mechanical drift of the telescope. We apply our formalism to a representative threemirror
anastigmat telescope and find quantitative relations between the second moments of the image and the
required stability of the telescope over a typical weak lensing observation.
We report on our recent laboratory results with the NASA/Goddard Space Flight Center (GSFC) Visible Nulling
Coronagraph (VNC) testbed. We have experimentally achieved focal plane contrasts of 1 x 108 and approaching 109 at
inner working angles of 2 * wavelength/D and 4 * wavelength/D respectively where D is the aperture diameter. The
result was obtained using a broadband source with a narrowband spectral filter of width 10 nm centered on 630 nm. To
date this is the deepest nulling result with a visible nulling coronagraph yet obtained. Developed also is a Null Control
Breadboard (NCB) to assess and quantify MEMS based segmented deformable mirror technology and develop and
assess closed-loop null sensing and control algorithm performance from both the pupil and focal planes. We have
demonstrated closed-loop control at 27 Hz in the laboratory environment. Efforts are underway to first bring the contrast
to > 109 necessary for the direct detection and characterization of jovian (Jupiter-like) and then to > 1010 necessary for
terrestrial (Earth-like) exosolar planets. Short term advancements are expected to both broaden the spectral passband
from 10 nm to 100 nm and to increase both the long-term stability to > 2 hours and the extent of the null out to a ~ 10 *
wavelength / D via the use of MEMS based segmented deformable mirror technology, a coherent fiber bundle,
achromatic phase shifters, all in a vacuum chamber at the GSFC VNC facility. Additionally an extreme stability
textbook sized compact VNC is under development.
We evaluate the feasibility of a balloon-borne nulling interferometer to detect and characterize an exosolar planet and the
surrounding debris disk. The existing instrument consists of a three-telescope Fizeau imaging interferometer with thre
fast steering mirrors and three delay lines operating at 800 Hz for closed-loop control of wavefront errors and fine
pointing. A compact visible nulling interferometer would be coupled to the imaging interferometer and in principle,
allows deep starlight suppression. Atmospheric simulations of the environment above 100,000 feet show that balloonborne
payloads are a possible path towards the direct detection and characterization of a limited set of exoplanets and
debris disks. Furthermore, rapid development of lower cost balloon payloads provide a path towards advancement of
NASA technology readiness levels for future space-based exoplanet missions. Discussed are the BENI mission and
instrument, the balloon environment and the feasibility of such a balloon-borne mission.
The Pupil-mapping Exoplanet Coronagraphic Observer (PECO) mission concept uses a coronagraphic 1.4-m
space-based telescope to both image and characterize extra-solar planetary systems at optical wavelengths.
PECO delivers 10-10 contrast at 2 λ/D separation (0.15") using a high-performance Phase-Induced Amplitude
Apodization (PIAA) coronagraph which remaps the telescope pupil and uses nearly all of the light coming into
the aperture. For exoplanet characterization, PECO acquires narrow field images simultaneously in 16 spectral
bands over wavelengths from 0.4 to 0.9 μm, utilizing all available photons for maximum wavefront sensing and
sensitivity for imaging and spectroscopy. The optical design is optimized for simultaneous low-resolution spectral
characterization of both planets and dust disks using a moderate-sized telescope. PECO will image the habitable
zones of about 20 known F, G, K stars at a spectral resolution of R≈15 with sensitivity sufficient to detect
and characterize Earth-like planets and to map dust disks to within a fraction of our own zodiacal dust cloud
brightness. The PIAA coronagraph adopted for PECO reduces the required telescope diameter by a factor of two
compared with other coronagraph approaches that were considered for Terrestrial Planet Finder Coronagraph
Flight Baseline 1, and would therefore also be highly valuable for larger telescope diameters. We report on
ongoing laboratory activities to develop and mature key PECO technologies, as well as detailed analysis aimed
at verifying PECO's wavefront and pointing stability requirement can be met without requiring development of
new technologies.
KEYWORDS: Cameras, Cryogenics, Photogrammetry, James Webb Space Telescope, Distortion, Error analysis, Metrology, Calibration, Received signal strength, Optical alignment
The alignment philosophy of the James Webb Space Telescope (JWST) Integrated Science Instrument
Module (ISIM) is such that the cryogenic changes in the alignment of the science instruments (SIs) and
telescope-related interfaces are captured in an alignment error budget. The SIs are aligned to the structure's
coordinate system under ambient, clean room conditions using laser tracker and theodolite metrology. The
ISIM structure is thermally cycled and temperature-induced mechanical and structural changes are
concurrently measured to ensure they are within the predicted boundaries.
We report on the ISIM photogrammetry system and its role in the cryogenic verification of the ISIM
structure. We describe the cryogenic metrology error budget and the analysis and testing that was
performed on the ISIM mockup, a full scale aluminum model of the ISIM structure, to ensure that the
system design allows the metrology goals to be met, including measurement repeatability and distortion
introduced from the camera canister windows.
DAVINCI is a dilute aperture nulling coronagraph that has the potential of directly detecting an Earth in the habitable zone around ~100 nearby stars. The novel feature of this mission concept is to replace a filled aperture 5-6 meter telescope with 4 by 1.1 meter
telescopes in a phased array, dramatically reducing the cost by
potentially by a factor of 5-10.
We have developed performance simulations for a precision attitude determination system using a focal plane star
tracker on an infrared space telescope. The telescope is being designed for the Destiny mission to measure
cosmologically distant supernovae as one of the candidate implementations for the Joint Dark Energy Mission. Repeat
observations of the supernovae require attitude control at the level of 0.010 arcseconds (0.05 microradians) during
integrations and at repeat intervals up to and over a year. While absolute accuracy is not required, the repoint precision is
challenging. We have simulated the performance of a focal plane star tracker in a multidimensional parameter space,
including pixel size, read noise, and readout rate. Systematic errors such as proper motion, velocity aberration, and
parallax can be measured and compensated out. Our prediction is that a relative attitude determination accuracy of 0.001
to 0.002 arcseconds (0.005 to 0.010 microradians) will be achievable. Attitude control will have a jitter of around 0.003
arcseconds and stability/repeatability to around 0.002 arcseconds.
Paul Scowen, Rolf Jansen, Matthew Beasley, Brian Cooke, Shouleh Nikzad, Oswald Siegmund, Robert Woodruff, Daniela Calzetti, Steven Desch, Alex Fullerton, John Gallagher, Sangeeta Malhotra, Mark McCaughrean, Robert O'Connell, Sally Oey, Debbie Padgett, James Rhoads, Aki Roberge, Nathan Smith, Daniel Stern, Jason Tumlinson, Rogier Windhorst
The Star Formation Observatory (SFO) is a 1.65m space telescope that addresses pivotal components in the 2007 NASA
Science Plan, with a primary focus on Cosmic Origins. The design under consideration provides 100 times greater
imaging efficiency and >10 times greater spectroscopic efficiency below 115 nm than existed on previous missions. The
mission has a well-defined Origins scientific program at its heart: a statistically significant survey of local, intermediate,
and high-redshift sites and indicators of star formation, to investigate and understand the range of environments,
feedback mechanisms, and other factors that most affect the outcome of the star and planet formation process. This
program relies on focused capabilities unique to space and that no other planned NASA mission will provide: near-
UV/visible (20-1100 nm) wide-field, diffraction-limited imaging; and high-efficiency, low- and high- resolution (R~40,000) UV (100-175 nm) spectroscopy using far-UV optimized coatings and recent advances in Micro-Channel Plate
(MCP) detector technology. The Observatory imager has a field of view in excess of 17' × 17' (>250 arcmin2) and uses a
dichroic to create optimized UV/blue and red/near-IR channels for simultaneous observations, employing detectors that
offer substantial quantum efficiency gains and that suffer lower losses due to cosmic rays.
The Pupil mapping Exoplanet Coronagraphic Observer (PECO) mission concept is a 1.4-m telescope aimed at
imaging and characterizing extra-solar planetary systems at optical wavelengths. The coronagraphic method
employed, Phase-Induced Amplitude Apodization or PIAA (a.k.a. pupil mapping) can deliver 1e-10 contrast at
2 lambda/D and uses almost all the starlight that passes through the aperture to maintain higher throughput and
higher angular resolution than any other coronagraph or nuller, making PECO the theoretically most efficient
existing approach for imaging extra-solar planetary systems. PECO's instrument also incorporates deformable
mirrors for high accuracy wavefront control. Our studies show that a probe-scale PECO mission with 1.4 m
aperture is extremely powerful, with the capability of imaging at spectral resolution R≈∠15 the habitable zones
of already known F, G, K stars with sensitivity sufficient to detect planets down to Earth size, and to map
dust clouds down to a fraction of our zodiacal cloud dust brightness. PECO will acquire narrow field images
simultaneously in 10 to 20 spectral bands covering wavelengths from 0.4 to 1.0 μm and will utilize all available
photons for maximum wavefront sensing and imaging/spectroscopy sensitivity. This approach is well suited for
low-resolution spectral characterization of both planets and dust clouds with a moderately sized telescope.
We also report on recent results obtained with the laboratory prototype of a coronagraphic low order wavefront
sensor (CLOWFS) for PIAA coronagraph. The CLOWFS is a key part of PECO's design and will enable high
contrast at the very small PECO inner working angle.
The Extrasolar Planetary Imaging Coronagraph (EPIC) is a NASA Astrophysics Strategic Mission Concept
under study for the upcoming Exoplanet Probe. EPIC's mission would be to image and characterize
extrasolar giant planets, and potential super-Earths, in orbits with semi-major axes between 2 and 10 AU.
EPIC will provide insights into the physical nature of a variety of planets in other solar systems
complimenting radial velocity (RV) and astrometric planet searches. It will detect and characterize the
atmospheres of planets identified by radial velocity surveys and potentially some transits, determine orbital
inclinations and masses, characterize the atmospheres of gas giants around A and F stars, observed the
inner spatial structure and colors of inner Spitzer selected debris disks. EPIC would be launched into a
heliocentric Earth trailing drift-away orbit, with a 3-year mission lifetime (5 year goal) and will revisit
planets at least three times.
The starlight suppression approach consists of a visible nulling coronagraph (VNC) that enables high order
starlight suppression in broadband light. To demonstrate the VNC approach and advance it's technology
readiness the NASA/Goddard Space Flight Center and Lockheed-Martin have developed a laboratory VNC
and have demonstrated white light nulling. We will discuss our ongoing VNC work and show the latest
results from the VNC testbed.
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%.
We have proposed the development of a low-cost space telescope, Destiny, as a concept for the NASA/DOE
Joint Dark Energy Mission. Destiny is a 1.65m space telescope, featuring a near-infrared (0.85-1.7m) survey
camera/spectrometer with a large flat-field Field Of View (FOV). Destiny will probe the properties of dark
energy by obtaining a Hubble diagram based on Type Ia supernovae (SN) and a large-scale mass power
spectrum derived from weak lensing distortions of field galaxies as a function of redshift.
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.
The Extrasolar Planetary Imaging Coronagraph (EPIC) is a proposed NASA Discovery mission to image
and characterize extrasolar giant planets in orbits with semi-major axes between 2 and 10 AU. EPIC will
provide insights into the physical nature of a variety of planets in other solar systems complimenting radial
velocity (RV) and astrometric planet searches. It will detect and characterize the atmospheres of planets
identified by radial velocity surveys, determine orbital inclinations and masses, characterize the
atmospheres around A and F type stars which cannot be found with RV techniques, and observe the inner
spatial structure and colors of debris disks. EPIC has a proposed launch date of 2012 to heliocentric Earth
trailing drift-away orbit, with a 3 year mission lifetime (5 year goal), and will revisit planets at least three
times at intervals of 9 months. The robust mission design is simple and flexible ensuring mission success
while minimizing cost and risk. The science payload consists of a heritage optical telescope assembly
(OTA), and visible nulling coronagraph (VNC) instrument. The instrument achieves a contrast ratio of 109
over a 4.84 arcsecond field-of-view with an unprecedented inner working angle of 0.14 arcseconds over the
spectral range of 440-880 nm, with spectral resolutions from 10 - 150. The telescope is a 1.5 meter offaxis
Cassegrain with an OTA wavefront error of λ/9, which when coupled to the VNC greatly reduces the
requirements on the large scale optics, compressing them to stability requirements within the relatively
compact VNC optical chain. The VNC features two integrated modular nullers, a spatial filter array (SFA),
and an E2V-L3 photon counting CCD. Direct null control is accomplished from the science focal
mitigating against complex wavefront and amplitude sensing and control strategies.
The CorECam Instrument Concept Study (ICS) addressed the requirements and science program for the
Terrestrial Planet Finder Coronagraph's (TPF-C) primary camera. CorECam provides a simple interface to
TPF-C's Starlight Suppression System (SSS) which would be provided by the TPF-C Program, and
comprises camera modules providing visible, and near-infrared (NIR) camera focal plane imaging. In its
primary operating mode, CorECam will conduct the core science program of TPF-C, detecting terrestrial
planets at visible wavelengths. CorECam additionally provides the imaging capabilities to characterize
terrestrial planets, and conduct an extended science program focused on investigating the nature of the
exosolar systems in which terrestrial planets are detected. In order to evaluate the performance of CorECam
we developed a comprehensive, end-to-end model using OSCAR which has provided a number of key
conclusions on the robustness of the TPF-C baseline design, and allows investigation of alternative
techniques for wavefront sensing and control. CorECam recommends photon counting detectors be
baselined for imaging with TPF-C since they provide mitigations against the background radiation
environment, improved sensitivity and facilitate alternative WFSC approaches.
Smithsonian Astrophysical Observatory (SAO) has set up a program to study coronagraphic techniques. The program consists of the development of new fabrication methods of occulter masks, characterization of the manufactured masks, and application of the masks to study speckle reduction technique. Our occulter mask fabrication development utilizes a focused ion beam system to directly shape mask profiles from absorber material. Initial milling trials show that we can shape nearly Gaussian-shaped mask profiles. Part of this development is the characterization of absorber materials, poly(methyl methacrylate) doped with light-stable chromophores. For the characterization of the masks we have built a mask scanner enabling us to scan the transmission function of occulter masks. The real mask transmission profile is retrieved applying the maximum entropy method to deconvolve the mask transmission function from the beam profile of the test laser. Finally, our test bed for studying coronagraphic techniques is nearing completion. The optical setup is currently configured as a classical coronagraph and can easily be re-configured for studying speckle reduction techniques. The development of the test bed control software is under way. This paper we will give an update of the status of the individual program elements.
An optical system capable of extremely high contrast imaging (about 10-10) at separations comparable to the
telescope's diffraction limit is critical for direct imaging of extrasolar terrestrial planets. The PIAA coronagraph
(Guyon 2003) based on pupil apodization by geometrical remapping of the flux in the pupil plane seems to be
especially adopted for the exoplanet imaging. Although this technique combines many of the advantages found
separately in other coronagraphs, two serious concerns remain unanswered: optics manufacturability and effects
of diffraction propagation. We describe here a hybrid PIAA/CPA (Classical Pupil Apodization) design in which
the apodization is shared between a remapping system (the main apodizer) and "classical" apodizers (auxillary
apodizers). In this scheme, optics become easier to manufacture and diffraction effects can be decreased to a
level consistent with a 10-10 PSF contrast in a wide spectral band. We show how the parameters of hybrid
PIAA/CPA system can be optimized and present some results of optical testing for the high optical quality
prototype of PIAA coronagraph.
The nulling coronagraph is one of 5 instrument concepts selected by NASA for study for potential use in the TPF-C
mission. This concept for extreme starlight suppression has two major components, a nulling interferometer to suppress
the starlight to ~10-10 per airy spot within 2 λ/D of the star, and a calibration interferometer to measure the residual
scattered starlight. The ability to work at 2 λ/D dramatically improves the science throughput of a space based
coronagraph like TPF-C. The calibration interferometer is an equally important part of the starlight suppression system.
It measures the measures the wavefront of the scattered starlight with very high SNR, to 0.05nm in less than 5 minutes
on a 5mag star. In addition, the post coronagraph wavefront sensor will be used to measure the residual scattered light
after the coronagraph and subtract it in post processing to 1~2x10-11 to enable detection of an Earthlike planet with a
SNR of 5~10.
The Phase-Induced Amplitude Apodization Coronagraph (PIAAC) uses a lossless beam apodization, performed
by aspheric mirrors, to produce a high contrast PSF. This concept offers a unique combination of high throughput
(almost 100%), high angular resolution (λ/D), small inner working angle (IWA = 1.5 λ/D), excellent achromaticity
(the apodization is performed by geometric reflection on mirrors) and low sensitivity to pointing errors or
stellar angular diameter. These characteristics make the PIAAC an ideal choice for direct imaging of extrasolar
terrestrial planets (ETPs) from space. We quantify the performance of the PIAAC and other coronagraph designs
both in terms of "raw" coronagraphic performance (throughput, IWA etc...) and number of stars around
which extrasolar terrestrial planets (ETPs) can be observed. We also identify the fundamental performance limit
that can be achieved by coronagraphy, and show that no other coronagraph design is as close to this limit as the
PIAAC. We find that in the photon noise limited regime, a 4m telescope with a PIAA coronagraph is able to
detect Earth-like planets around 30 stars with 1hr exposure time per target (assuming 25% throughput and exozodi
levels similar to our solar system). With a smaller 1 to 2-m diameter telescope, more massive rocky planets
could be detected in the habitable zones of a few nearby stars, and an imaging survey of Jupiter-like planets
could be performed. Laboratory results and detailed simulations confirm the large potential of this concept for
direct imaging of ETPs. A prototype high contrast PIAAC system is currently being operated to demonstrate
the coronagraph's performance.
SAO has set up a testbed to study coronagraphic techniques, starting with Labeyrie's multi-step speckle reduction technique. This technique expands the general concept of a coronagraph by incorporating a speckle corrector (phase and/or amplitude) in combination with a second occulter for speckle light suppression. Here we are describing the initial testbed configuration. In addition, the testbed will be used to test a new approach of the phase diversity method to retrieve the speckle phase and amplitude. This method requires measurements of the speckle pattern in the focal plane and slightly out-of-focus. Then we will calculate a phase of the wave from which we can derive a correction function for the speckle corrector. Furthermore we report results from a parallel program which studies new manufacturing methods of soft-edge occulter masks. Masks were manufactured using the spherical caps method. Since the results were not satisfying we also investigated the method of ion beam milling of masks. Here we will present the outline of this method. Masks manufactured with both methods will be fully characterized in our mask tester before their use in the testbed.
The Hubble Space Telescope (HST) continues to provide spectacular views into the universe. Its findings have profoundly affected mankind's view of itself by revealing to scientist and layperson alike many previously unimaginable discoveries. These result from the technical capability of HST. This 2.4-meter aperture diameter telescope includes imaging, spectroscopic, as well as limited coronagraphic instrumentation. Current plans (as of 2/8/2005) are to operate HST until later this decade, without servicing, and then deorbit it in a controlled manner early next decade. Cost effective, 2.4 meter, near term replacements for HST are under study as part of the NASA sponsored Origin Probe studies. TPF-C, scheduled for launch in mid-next decade, will develop the large mirror technology that could enable a next generation UV/Optical/NIR facility. The next generation facility would be a very large aperture collector telescope with wide field of view (FOV) imagery, precise wavefront control, and high ultraviolet efficiency. The facility would provide spectroscopic capability in addition to imagery. This paper will explore design trades and configurations applicable to a future expanded HST.
A hardware demonstration has been performed in which a nominally flat, complex aspheric mirror is used to correct the high-order aberrated wavefront error of an off-axis parabolic mirror to 0.5 nm rms. The purpose of the project is to demonstrate the viability of using a static, aspheric optic to correct a telescope wavefront to the degree needed for detection of extra-solar Jovian planets. The demonstration procedure and test results are presented.
Amplitude apodization of a telescope's pupil can be used to reduce the diffraction rings (Airy rings) in the PSF to allow high contrast imaging. Rather than achieving this apodization by selectively removing light at the edges of the pupil, we propose to produce the desired apodized pupil by redistributing the pupil's light. This lossless apodization concept can yield a high contrast PSF which allows the efficient detection of Earth-sized planets around stars at ~10pc with a 2m visible telescope in space. We review the current status of a JPL-funded study of this concept for the Terrestrial Planet Finder (TPF) mission, including a lab experiment and extensive computer simulations.
KEYWORDS: Coronagraphy, Diffraction, Planets, Wave propagation, Radio propagation, Chemical elements, 3D modeling, Finite element methods, Waveguides, Light
In this work we study vector electromagnetic wave propagation in a visible-light coronagraph for applications to the design and analysis of Terrestrial Planet Finder (TPF). A visible light coronagraph in TPF requires detection of a terrestrial planet which is ~1010 dimmer than the central stellar source. Consequently, any theory used to design and analyze TPF requires accuracy better than 10-10 in intensity or 10-5 in electric field.
Current coronagraphic approaches to TPF have relied on scalar diffraction theory. However, the vector nature of light requires a vector approach to the problem. In this study we employ a time-harmonic vector theory to study the electromagnetic field propagation through metallic focal plane occulting mask on dielectric substrate. We use parallelized edge-based vector finite element model to compute the wave propagation in a three-dimensional tetrahedral grid representing the geometry of the coronagraph. The edge-based finite element method overcomes the problem of modal propagation and rigorously enforces the field divergence to be zero. The reflectivity and transmittivity in the geometry are computed through the gold metal in various shapes using a planar incident beam. Subsequently, the near-field beam diffraction around the mask is investigated.
The Dark Energy Space Telescope (DESTINY) is a proposed approach to the Joint Dark Energy Mission (JDEM). This paper describes its current design and trades of an on-going mission concept study. The DESTINY ~1.8-meter near-infrared (NIR) grism-mode space telescope would gather a census of type Ia and type II supernovae (SN) over the redshift range 0.5<Z<1.7 for characterizing the nature of dark energy. The central concept is a wide-field, all-grism NIR survey camera. Grism spectra with 2-pixel resolving power λ/Δλ≈ 100 will provide broadband spectrophotometry, redshifts, SN classification, as well as valuable time-resolved diagnostic data for understanding the SN explosion physics. DESTINY provides simultaneous spectroscopy on each object within the wide field-of-view sampled by a large focal plane array. The design combines the wide FOV coverage of a flat field, all-reflective three mirror anastigmat with spectroscopy using an optimized nonobjective "objective" grism located in the real exit pupil of the TMA. The spectra from objects within the resulting 0.25 square-degree FOV are sampled with 100 mas pixels by an 8k x 32k HgCdTe FPA. This methodology requires only a single mode of operation, a single detector technology, and a single instrument.
KEYWORDS: Space telescopes, Near infrared, Distance measurement, Large Synoptic Survey Telescope, Cameras, Physics, Spectroscopy, Hubble Space Telescope, Atmospheric modeling, Photometry
The Destiny space telescope is a candidate architecture for the NASA-DOE Joint Dark Energy Mission (JDEM). This paper describes some of the scientific and observational issues that will be explored as part of our mission concept study. The Destiny ~1.8-meter near-infrared (NIR) grism-mode space telescope would gather a census of type Ia and type II supernovae (SN) over the redshift range 0.5 < z < 1.7 for measuring the expansion rate of the Universe as a function of time and characterizing the nature of dark energy. The central concept is a wide-field, all-grism NIR survey camera. Grism spectra with 2-pixel resolving power R~70-100 will provide broad-band spectrophotometry, redshifts, SN classification, as well as valuable time-resolved diagnostic data for understanding the SN explosion physics. Spectra from all objects within the 1° x 0.25° FOV will be obtained on a large HgCdTe focal plane array. Our methodology requires only a single mode of operation, a single detector technology, and a single instrument.
The Extrasolar Planetary Imaging Coronagraph (EPIC) will provide the first direct measurements of a broad range of fundamental physical characteristics of giant planets in other solar systems. These characteristics include orbital inclination, mass, brightness, color, the presence (or absence) of CH4 and H2O, and orbital or rotational-driven variability. EPIC utilizes a 1.5 meter telescope coupled to a Visible Nulling Coronagraph to achieve these science goals. EPIC has been proposed as a Discovery Mission.
The Wide Field Camera 3 (WFC3) instrument was designed and built to replace the Hubble Space Telescope (HST) instrument Wide Field and Planetary Camera 2 (WFPC2) and to provide improved ultra-violet through near infra-red imaging capability during the extended HST mission. The WFC3 instrument consists of a two-channel instrument providing diffraction-limited imaging across an average 160 arc second square field of view over 200 to 1000 nm on a 4k x 4k Si detector and an average 135 arc second square field of view over 850 to 1700 nm on a 1k x 1k HgCdTe detector. We describe the optical design and predicted performance of WFC3.
George Rieke, Erick Young, James Cadien, Charles Engelbracht, Karl Gordon, Douglas Kelly, Frank Low, Karl Misselt, Jane Morrison, James Muzerolle, G. Rivlis, John Stansberry, Jeffrey Beeman, Eugene Haller, David Frayer, William Latter, Alberto Noriega-Crespo, Deborah Padgett, Dean Hines, J. Douglas Bean, William Burmester, Gerald Heim, Thomas Glenn, R. Ordonez, John Schwenker, S. Siewert, Donald Strecker, S. Tennant, John Troeltzsch, Bryce Unruh, R. Warden, Peter Ade, Almudena Alonso-Herrero, Myra Blaylock, Herve Dole, Eiichi Egami, Joannah Hinz, Emeric LeFloch, Casey Papovich, Pablo Perez-Gonzalez, Marcia Rieke, Paul Smith, Kate Su, Lee Bennett, David Henderson, Nanyao Lu, Frank Masci, Misha Pesenson, Luisa Rebull, Jeonghee Rho, Jocelyn Keene, Susan Stolovy, Stefanie Wachter, William Wheaton, Paul Richards, Harry Garner, M. Hegge, Monte Henderson, Kim MacFeely, David Michika, Chris Miller, Mark Neitenbach, Jeremiah Winghart, R. Woodruff, E. Arens, Charles Beichman, Stephen Gaalema, Thomas Gautier, Charles Lada, Jeremy Mould, Gerry Neugebauer, Karl Stapelfeldt
The Multiband Imaging Photometer for Spitzer (MIPS) provides long wavelength capability for the mission, in imaging bands at 24, 70, and 160 microns and measurements of spectral energy distributions between 52 and 100 microns at a spectral resolution of about 7%. By using true detector arrays in each band, it provides both critical sampling of the Spitzer point spread function and relatively large imaging fields of view, allowing for substantial advances in sensitivity, angular resolution, and efficiency of areal coverage compared with previous space far-infrared capabilities. The Si:As BIB 24 micron array has excellent photometric properties, and measurements with rms relative errors of 1% or better can be obtained. The two longer wavelength arrays use Ge:Ga detectors with poor photometric stability. However, the use of 1.) a scan mirror to modulate the signals rapidly on these arrays, 2.) a system of on-board stimulators used for a relative calibration approximately every two minutes, and 3.) specialized reduction software result in good photometry with these arrays also, with rms relative errors of less than 10%.
Optical coronagraphy is a promising possibility for finding and characterizing Earth-like planets that orbit nearby stars. This approach begins with a large unobscured conventional telescope, but significant modifications are needed to achieve adequate suppression of the glare of the star. Three techniques are under consideration for suppression of the aperture diffraction which redirects starlight into the planet's pixel; once this is satisfied, extraordinary precision and stability in the wavefront are needed as well to suppress scatter of the starlight into that pixel. We discuss the central choices in the setting of error budgets, a summary of key allocations in that budget, optical model results that demonstrate the operation and performance of the system, and key hardware requirements.
A concept is presented for a 10-meter sparse aperture hypertelescoep to detect extrasolar planets by direct imaging from the ground through the turbulent atmosphere. The telescope achieves high dynamic range with good image quality very close to bright stellar sources using pupil densification techniques and real-time atmospheric correction. Active correction of the perturbed wavefront is greatly simplified by several unique design features of the telescope: 1) use of an array of 19 small subaperture flat mirrors, 2) mounting the flats on a steerable parabolic truss structure, 3) operating in the near-IR, and 4) making the subaperture flats comparable in size to the seeing cells. These features relax the requirements on the wavefront sensing and control system. This paper describes the general concept. The details of design and implementation will be addresed separately.
The Extrasolar Planet Observatory (ExPO) is envisioned as a Discovery-class space telescope for the direct detection and characterization of extra-solar planets. ExPO would also demonstrate the feasibility of a number of technologies which could be critical to the ultimate success of the Terrestrial Planet Finder mission. ExPO would detect a wide range of planet types in the visible and near IR, and do spectrophotometry and spectroscopy on many of the detected objects. The apoodized square aperture coronagraphic space telescope is designed to resolve faint companions near much brighter point-like sources by achieving very high dynamic range imaging at separations as small as 0.1 arcsec.
The Jovian Planet Finder (JPF) is a proposed NASA MIDEX mission to place a highly optimized coronagraphic telescope on the International Space Station (ISS) to image Jupiter-like planets around nearby stars. The optical system is an off-axis, unobscured telescope with a 1.5 m primary mirror. A classical Lyot coronagraph with apodized occulting spots is used to reduce diffracted light from the central star. In order to provide the necessary contrast for detection of a planet, scattered light from mid-spatial-frequency errors is reduced by using super-smooth optics. Recent advances in polishing optics for extreme-ultraviolet lithography have shown that a factor of >30 reduction in midfrequency errors relative to those in the Hubble Space Telescope is possible (corresponding to a reduction in scattered light of nearly 1000x). The low level of scattered and diffracted light, together with a novel utilization of field rotation introduced by the alt-azimuth ISS telescope mounting, will provide a relatively low-cost facility for not only imaging extrasolar planets, but also circumstellar disks, host galaxies of quasars, and low-mass substellar companions such as brown dwarfs.
We present an overview of the ACS on-orbit performance based on the calibration observations taken during the first three months of ACS operations. The ACS meets or exceeds all of its important performance specifications. The WFC and HRC FWHM and 50% encircled energy diameters at 555 nm are 0.088" and 0.14", and 0.050" and 0.10". The average rms WFC and HRC read noises are 5.0 e- and 4.7 e-. The WFC and HRC average dark currents are ~ 7.5 and ~ 9.1 e-/pixel/hour at their operating temperatures of - 76°C and - 80°C. The SBC + HST throughput is 0.0476 and 0.0292 through the F125LP and F150LP filters. The lower than expected SBC operating temperature of 15 to 27°C gives a dark current of 0.038 e-/pix/hour. The SBC just misses its image specification with an observed 50% encircled energy diameter of 0.24" at 121.6 nm. The ACS HRC coronagraph provides a 6 to 16 direct reduction of a stellar PSF, and a ~1000 to ~9000 PSF-subtracted reduction, depending on the size of the coronagraphic spot and the wavelength. The ACS grism has a position dependent dispersion with an average value of 3.95 nm/pixel. The average resolution λ/Δλ for stellar sources is 65, 87, and 78 at wavelengths of 594 nm, 802 nm, and 978 nm.
The Hubble Space Telescope (HST) has provided superb imaging and spectroscopic capability for studying galaxies, stars, and nebulae in the ultraviolet and visible (UVIS) wavelength regions, as well as in the near infrared. The HST is a 2.4-meter telescope with imaging, spectroscopic, and limited coronagraphic instrumentation. NASA plans to discontinue its operations in 2010. Next generation ultraviolet and visible telescope capability to replace HST is currently under discussion. The new facility would include a very large aperture collector, ultra wide field of view (WFOV) imagery, precise wavefront control, and high UVIS efficiency. Such a facility would combine ultra wide FOV imagery that is diffraction-limited at Lyman-α (λ = 122 nm) with efficient broad spectral coverage. The design must also provide spectroscopic, and possibly coronagraphic, capability in addition to imagery. This paper will discuss design trades for such capabilities and present design configurations. The paper will also identify key technologies needed to support the implementation of the new facility.
Navakanta Bhat, Harry Chuang, Paul Tsui, R. Woodruff, John Grant, R. Kruth, Asanga Perera, Stephen Poon, Sean Collins, D. Dyer, Veena Misra, I. Yang, Suresh Venkatesan, Percy Gilbert
In this paper, we compare four different approaches for transistor design for the 0.25 micrometer technology from the point of view of performance, stand-by power and ease of manufacturing. For the high performance logic applications such as high end microprocessors, 0.18 micrometer transistor (Lgate equals 0.18 plus or minus 0.02 micrometer) with super steep retrograde wells and halo implants but without extension implants can achieve maximum frequency of operation (Fmax) exceeding 380 Mhz for the 0.25 micrometer technology. On the other hand, for low power applications such as mobile communication equipments, a different 0.22 micrometer (Lgate equals 0.22 plus or minus 0.02 micrometer) transistor design which simplifies manufacturing process by eliminating two photolithography steps becomes more attractive. The four transistor designs are compared using CV/I metric and manufacturability trade-offs are discussed.
Over the past two years, a team of researchers led by the Goddard Space Flight Center has developed a conceptual design for the NGST. The optical design of the optical telescope assembly (OTA) as well as the integrated science instrument module (ISIM) has presented many challenges. As currently envisioned, the NGST is an 8 m class telescope capable of diffraction-limited imaging at a wavelength of 2 microns operating at L2 at a temperature of around 40 K. The baseline design incorporates features such as a segmented primary mirror, deployable optical components, and active optics including a deformable mirror and fast steering mirror. In this paper, we describe the development of the conceptual design, discuss the trade-offs involving performance versus complexity, packaging, and cost, and then highlight some of the more important lessons that have been learned in the process. The interaction between the OTA and the ISIM is also discussed. It is hoped that this paper can provide insight and/or guidance to those who ar or will be working on the continuing refinement of the optical design of the NGST.
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 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 advanced camera for surveys, designed to be installed in 1999 during the third servicing mission of the Hubble Space Telescope, is a high performance axial bay camera.
The Advanced Camera for the Hubble Space Telescope has three cameras. The first, the Wide Field Camera, will be a high- throughput, wide field, 4096 X 4096 pixel CCD optical and I-band camera that is half-critically sampled at 500 nm. The second, the High Resolution Camera (HRC), is a 1024 X 1024 pixel CCD camera that is critically sampled at 500 nm. The HRC has a 26 inch X 29 inch field of view and 29 percent throughput at 250 nm. The HRC optical path includes a coronagraph that will improve the HST contrast near bright objects by a factor of approximately 10 at 900 nm. The third camera, the solar-blind camera, is a far-UV, pulse-counting array that has a relatively high throughput over a 26 inch X 29 inch field of view. The advanced camera for surveys will increase HST's capability for surveys and discovery by a factor of approximately 10 at 800 nm.
We describe the instrument package concept that we have investigated as part of the Goddard Space Flight Center study for NGST. It is composed of highly integrated, high performance cameras and spectrometers covering the spectral region from 0.6 to 30 microns and with a large field of view.the suite has been configured to reduce cost and complexity with no sacrifice in scientific merit. A common optical bench minimizes interfaces, a guiding system integrated in the science module makes use of the science cameras with minimal penalty to science, and all near IR instruments are built around the same detector module.
The Next Generation Space Telescope (NGST) is currently being designed during a pre-phase A study in cooperation with the NASA Goddard Space Flight Center (GSFC) led team. Ball Aerospace and Technologies Corporation is leading one of two competitive GSFC funded pre-phase A studies of mission architectures for NGST. The NGST is the next major NASA astronomy mission following HST and SIRTF. NGST will be an observatory providing zodiacal light background limited 1-5 micron imagery and spectroscopy using a passively cooled 6 to 8 meter diameter telescope. The stretch goals specify imagery and spectroscopy in the 5 to 30 micron region and shortward of 1 micron. While emphasizing science return and maintaining simplicity, we have arrived at a configuration of a highly reliable mission architecture that achieves the desired science including many of the stretch science goals. This paper will describe the process and major trades we used to arrive at the system configuration, our current configuration and some of the key remaining trade-offs.
Advanced optical bandpass filters for the Hubble Space Telescope (HST) advanced camera for surveys (ACS) have been developed on a filer-by-filter basis through detailed studies which take into account the instrument's science goals, available optical filter fabrication technology, and developments in ACS's charge-coupled-device detector technology. These filters include a subset of filters for the Sloan Digital Sky Survey which are optimized for astronomical photometry using today's charge-coupled- devices. In order for ACS to be truly advanced, these filters must push the state-of-the-at in performance in a number of key areas at the same time. Important requirements for these filters include outstanding transmitted wavefront, high transmittance, uniform transmittance across each filter, spectrally structure-free bandpasses, exceptionally high out of band rejection, a high degree of parfocality, and immunity to environmental degradation. These constitute a very stringent set of requirements indeed, especially for filters which are up to 90 mm in diameter. The highly successful paradigm in which final specifications for flight filters were derived through interaction amongst the ACS Science Team, the instrument designer, the lead optical engineer, and the filter designer and vendor is described. Examples of iterative design trade studies carried out in the context of science needs and budgetary and schedule constraints are presented. An overview of the final design specifications for the ACS bandpass and ramp filters is also presented.
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 Advanced Camera for the Hubble Space Telescope will have three cameras. The first, the Wide Field Camera, will be a high throughput (45% at 700 nm, including the HST optical telescope assembly), wide field (200' X 204'), optical and I-band camera that is half critically sampled at 500 nm. The second, the High Resolution Camera (HRC), is critically sampled at 500 nm, and has a 26' X 29' field of view and 25% throughput at 600 nm. The HRC optical path will include a coronagraph which will improve the HST contrast near bright objects by a factor of approximately 10. The third camera is a far ultraviolet, Solar-Blind Camera that has a relatively high throughput (6% at 121.6 nm) over a 26' X 29' field of view. The Advanced Camera for Surveys will increase HST's capability for surveys and discovery by at least a factor of ten.
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.