We describe our technical approach to developing a space observatory to survey the large-scale distribution of neutral and ionized intergalactic gas during cosmological reionization (the landmark event of “Cosmic Dawn”) from 400 to 800 million years after the Big Bang. To look this far back in time at the large-scale distributions of ionized gases, we use wide-field, narrow-passband surveys for Lyman alpha light from individual galaxies red-shifted to the near-infrared. Wherever this light can be seen, it implies the presence of ionized gas. We are developing a large FOV (0.5-to-1.0-degree) instrument with plate scale on the order of 0.3”/pixel to obtain a comprehensive view of the reionization process over a representative volume of the early universe. To maximize science return, the Reionization Explorer (REX) will be placed in a high orbit. Through disciplined application of design-for-cost principles and a thorough searching for existing designs that can achieve our science objectives, we have developed what could be a game changing approach at advancing our understanding of the formation of the universe on a limited Small Explorer (SMEX) budget by leveraging existing telescope, instrument, and spacecraft designs.
REX is a NASA Astrophysics Small Explorer Mission concept to chart the history of cosmic dawn in unprecedented detail in space and time. REX will identify very young galaxies and black holes by means of their powerful Lyman alpha (Lyα) line emission using about 10 narrow-bandpass filters covering about 100 square degrees. The strong line emission identifies samples of the most actively star-forming early galaxies, believed to be the drivers of reionization. Moreover, mapping the distribution and properties of the Lyman alpha emitting population will reveal the distribution of ionized and neutral gas, because neutral gas scatters Lyman alpha light, rendering them difficult to detect. REX will use an 0.5-1m telescope and 1 square degree field of view, tiled with HgCdTe detectors with development heritage from the Nancy Grace Roman Space Telescope. Its large, flexible filter complement will be used in a point-and-stare mode to identify Lyα emitting galaxies at a range of discrete redshift slices spanning the reionization era. In addition to its core reionization surveys, REX brings a new capability of tracing gas emission over large scales at the peak of star and black formation era. We will find millions of the youngest, least massive galaxies in epochs spanning the most active growth period of the universe. Applications will include ionized gas in nearby and distant galaxies, active galactic nuclei, and galaxy clusters. In summary, the REX survey will have the sensitivity and the area coverage to find the sites of earliest galaxy formation and will have the pixel size to enable good localization for follow up of individual galaxies with JWST and future telescopes.
What is the amount of ionizing energy incident on exoplanet atmospheres from their host stars? What is the relationship between white-light flares and this ionizing energy? These are key questions required to link our current archive of hundreds of stellar whitelight flares to the ionizing radiation released during them, and the ramifications of those flares on the survival of exoplanetary atmospheres, particularly for planets orbiting within the habitable zones of low-mass stars. The Small NASA Optical Ultraviolet Telescope (SNOUT) is a proposed Pioneers mission comprised of two co-pointing telescopes: one optimized for EUV wavelengths (comprised of three separate EUV segments) and one for visible wavelengths. SNOUT is designed to measure the quiescent extreme-UV (EUV) emission for 30 mow-mass stars (0.3 - 1 solar masses), covering a range of ages, in three EUV bandpasses. The combined instrument is housed in an ESPA-Grande spacecraft and will launch into low Earth orbit for a one-year baseline mission. SNOUT has a substantial educational and early-career mentoring component; early-career scientists and engineers comprise more than half of the team, including key leadership roles.
The ORCAS Keck Instrument Demonstrator (ORKID) is a visible-light diffraction-limited camera that was installed behind the WMKO Keck II AO system in the fall of 2022. Its primary purpose is to act as a pathfinder instrument for adaptive optics-fed visible-light imaging at Keck, with consideration for upcoming AO upgrades and future possibilities. ORKID is diffraction-limited down to 650nm and can operate with millisecond frame rates, enabling frame selection and frame registration in post-processing. Here we provide an overview of the commissioning of the instrument and describe its on-sky performance. Using Keck’s current AO deformable mirror, and its Shack-Hartmann and pyramid wavefront sensors, we are able to achieve images with point-spread function cores of 15-17 milliarcseconds FWHM. We report here on early observations obtained within the first year of operations and we provide a gallery of scientific objects of interest with ORKID, as a preview for future capabilities.
The Orbiting Configurable Artificial Star (ORCAS) mission in collaboration with the W. M. Keck Observatory (WMKO) is poised to deliver near diffraction limited observations in visible light. The ability to conduct such observations will enable significant scientific discoveries in fields related to Active Galactic Nuclei (AGN), Dark Energy, Flux Calibration, the High Redshift Universe, Exoplanets, and the Solar System. The ORCAS team has successfully completed three primary mission development goals to enable such observations. The performance demonstration with the ORCAS Keck Instrument Demonstrator (ORKID) captured arguably the highest resolution image at visible wavelengths from a large (10 meter) segmented telescope on the ground to date. High resolution AO imaging of the galaxy UGC 4729 in Natural Guide Star (NGS) mode was performed by locking onto a foreground asteroid passing nearby, which simulated an observation with a moving guide star validating post processing capabilities and demonstrating how regions unreachable by NGS and LGS could be explored. Additionally, the ORCAS team has successfully locked onto a laser source onboard the Laser Communications Relay Demonstration (LCRD) and closed the adaptive optics loop to perform near diffraction limited imaging at 1550 nm with the Keck 10 meter, the first demonstration of such capability with a large segmented telescope. All of these results validate the feasibility of the ORCAS mission. Following these accomplishments, ORCAS will be strongly positioned to propose a full-scale mission to upcoming opportunities.
We have designed an Integral Field Unit for the ORCAS Keck Instrument Development II (ORKID II) Instrument. Building on the success of the ORKID camera which achieved 15.2 masec PSF FWHM visible light imaging, ORKID II will add Integral Field Spectroscopy to analyze Active Galactic Nuclei (AGN), supernovae redshift and brightness, and other observations. Several design options have been explored based on image slicers manufactured by the Canon Corporation’s machining process. Field layouts can include up to three disparate spatial sampling, with a lower limit of 6.7 masec. Spectral resolutions are considered from R 100 to R 10,000.
Publishers Note: This paper, and video were originally published on 14 December 2020, both were replaced with a corrected/revised version on 9 April 2020. If you downloaded the original PDF but are unable to access the revision, please contact SPIE Digital Library Customer Service for assistance.
As part of its technology demonstration, the Nancy Grace Roman Space Telescope (RST) Coronagraph Instrument (CGI) will demonstrate point source spectroscopy and polarization measurements of disks. The specific implementation of spectroscopy is a zero-deviation Amici prism and a slit to be placed on the planet after high contrast has been achieved by CGI. The polarization optics are a set of Wollaston prisms so that orthogonal polarization states can be measured simultaneously. The CGI spectral characterization mode, being designed and built and Goddard Space Flight Center (GSFC), has a spectral resolution of R50 at its central wavelength and is designed to accommodate a 15% bandpass spanning 610785nm. In order to recover Stokes information, there are two sets of Wollaston prisms clocked 45 degrees with respect to one another with each measurement taken in series. The Wollaston design and optical elements are a contribution by the Japanese Aerospace Exploration Agency (JAXA), with final alignment and testing being done at GSFC. The spectroscopy mode is designed to target Methane absorption features around 730nm, keeping the spectral resolution as low as possible to improve the signal-to-noise ratio and hence reduce detection time. We highlight the requirements for these modes and address the challenge of on-orbit spectral calibration for a deployable slit in the presence of pointing drifts. Of unique interest is how the observatory error budget couples into good stellar spectrum calibration and subsequent speckle subtraction. We also provide further detail on the optomechanical design, its modeled performance, and operations concept. These performance metrics are simulated to demonstrate how a slit located at an arbitrary field point is homed onto the planet and converted to a calibrated spectrum.
A highly integrated Concurrent Engineering Team (CET) within a flight project evolves in its function and has the potential to provide many benefits through the project lifecycle. The benefits include superior systems-oriented design products, as well as overall improved project efficiency and higher-performing interpersonal relationships within the project. If physically integrated, this can manifest as a Concurrent Engineering Center (CEC) centrally located within a project’s physical office space. Here we discuss the process to establish and maintain a tightly integrated engineering and design team for providing highly streamlined service to the project, including a cost/benefits analysis discussion.
The WFIRST wide field instrument (WFI) includes a slitless spectrometer, which plays an important role in the WFIRST mission for the survey of emission-line galaxies. WFI is building engineering design and environmental test (EDU and ETU) units to reduce risk for the flight grism unit. We report here on successful build and test of the EDU grism. The four-element EDU grism consists of two prism elements and two diffractive elements that provide R700 dispersion. The elements were fabricated with alignment fiducials and integral flats to allow opto-mechanical alignment in six-degrees of freedom. Each element in turn, was installed onto a hexapod and positioned to its nominal orientation relative to the grism deck, then bonded into individual cells. Alignment measurements were performed in situ using theodolites to set tip/tilt and a Micro-vu non-contact Multisensor Measurement System was used to set despace, decenter and clocking of each element using the hexapod. After opto-mechanical alignment, the grism wavefront was measured using an Infrared ZYGO interferometer at various field points extending over a 20 by 14- degree (local) field of view. Using modeled alignment sensitivities, we determined the alignment correction required on our Element 2 prism compensator and successfully minimized the field dependent wavefront error and confocality. This paper details the alignment and testing of the EDU grism at ambient and cold operating temperatures.
Now in Phase-B, the architecture of the Wide-Field Infra-Red Survey Telescope (WFIRST) payload has matured since 2013 to accommodate various opto-mechanical constraints. Based on a 2.4-meter aperture Forward Optical Assembly (FOA), the Imaging Optics Assembly (IOA) provides corrected optical fields to each on-board instrument. Using a Three Mirror Anastigmat (TMA) optical design, the Wide-Field Channel (WFC) provides ~1/3-square degree of instantaneous field coverage at 0.11 arcsecond pixel scale. The WFC as-built predictive analysis anticipates near diffraction-limited imaging over a focal plane of 300.8 million pixels, operating in seven panchromatic bands between 0.48 – 2.0μm, or a 1-octive multi-spectral imaging mode from ~0.95-1.93μm. The IOA provides the Coronagraph Instrument (CGI) a collimated beam with very specific wavefront constraints. We present configuration changes since 2013 that improved interfaces, improved testability, and reduced technical risk. We provide an overview of our Integrated Modeling results, performed at an unprecedented level for a phase-A study, to illustrate performance margins with respect to static wavefront error, jitter, and thermal drift.
NASA’s Wide Field Infrared Survey Telescope (WFIRST) is being designed to deliver unprecedented capability in dark energy and exoplanet science, and to host a technology demonstration coronagraph for exoplanet imaging and spectroscopy. The observatory design has matured since 2013 [“WFIRST 2.4m Mission Study”, D. Content, SPIE Proc Vol 8860, 2013] and we present a comprehensive description of the WFIRST observatory configuration as refined during formulation phase (AKA the phase-A study). The WFIRST observatory is based on an existing, repurposed 2.4m space telescope coupled with a 288 megapixel near-infrared (0.6 to 2 microns) HgCdTe focal plane array with multiple imaging and spectrographic modes. Together they deliver a 0.28 square degree field of view, which is approximately 100 times larger than the Hubble Space Telescope, and a sensitivity that enables rapid science surveys. In addition, the technology demonstration coronagraph will prove the feasibility of new techniques for exoplanet discovery, imaging, and spectral analysis. A composite truss structure meters both instruments to the telescope assembly, and the instruments and the spacecraft are on-orbit serviceable. We present the current design and summarize key Phase-A trade studies and configuration changes that improved interfaces, improved testability, and reduced technical risk. We provide an overview of our Integrated Modeling results, performed at an unprecedented level for a phase-A study, to illustrate performance margins with respect to static wavefront error, jitter, and thermal drift. Finally, we summarize the results of technology development and peer reviews, demonstrating our progress towards a low-risk flight development and a launch in the middle of the next decade.
The WFIRST Wide-Field Infrared Survey Telescope TMA optical design provides 0.28-sq° FOV at 0.11” pixel scale to the Wide Field Instrument, operating between 0.48-2.0μm, including a spectrograph mode (1.0-2.0μm.) An Integral Field Channel provides 2-D discrete spectroscopy at 0.15” and 0.3” sampling from 0.42-2.0μm.
WFIRST is one of NASA’s Decadal Survey Missions and is currently in Phase-A development. The optical design of the WFIRST Integral Field Channel (IFC), one of three main optical channels of WFIRST, is presented, and the evolution of the IFC channel since the Mission Concept Review (MCR, end of Pre-Phase A) is discussed. The IFC has two subchannels: Supernova (IFC-S) and Galaxy (IFC-G) channels, with Fields of View of 3”x4.5” and 4.2”x9” respectively, and ~R 100 spectral analysis over waveband 0.42–2.0 μm. The Phase-A IFC optical design meets image quality requirements over the field of view (FOV) while balancing cost and volume constraints.
KEYWORDS: Space telescopes, Telescopes, Mirrors, Infrared telescopes, Space operations, Optical telescopes, Coronagraphy, Monte Carlo methods, Infrared astronomy, Infrared radiation
The Wide-Field Infrared Survey Telescope (WFIRST) mission[1] is the top-ranked large space mission in the New Worlds, New Horizon (NWNH) Decadal Survey of Astronomy and Astrophysics. WFIRST will settle essential questions in both exoplanet and dark energy research and will advance topics ranging from galaxy evolution to the study of objects within the galaxy. The WFIRST mission uses a repurposed 2.4-m Forward Optical Telescope assembly (FOA), which, when completed with new aft optics will be an Integrated Optical Assembly (IOA). WFIRST is equipped with a Wide Field Instrument (WFI) and a Coronagraph Instrument (CGI). An Instrument Carrier (IC) meters these payload elements together and to the spacecraft bus (S/C). A distributed ground system receives the data, uploads commands and software updates, and processes the data. After transition from the study phase, Pre-Phase-A (a.k.a., “Cycle 6”) design to NASA Phase A formulation, a significant change to the IOA was initiated; including moving the tertiary mirror from the instrument package to a unified three-mirror anastigmat (TMA) placement, that provides a wide 0.28-sq° instrumented field of view to the Wide Field Instrument (WFI). In addition, separate relays from the primary and secondary mirror feed the Wide Field Instrument (WFI) and Coronagraph Instrument (CGI). During commissioning the telescope is aligned using wavefront sensing with the WFI[2]. A parametric and Monte-Carlo analysis was performed, which determined that alignment compensation with the secondary mirror alone degraded performance in the other instruments. This led to the addition of a second compensator in the WFI optical train to alleviate this concern. This paper discusses the trades and analyses that were performed and resulting changes to the WFIRST telescope architecture.
The slitless spectrometer plays an important role in the WFIRST mission for the survey of emission-line galaxies. This
will be an unprecedented very wide field, HST quality 3D survey of emission line galaxies1. The concept of the
compound grism as a slitless spectrometer has been presented previously. The presentation briefly discusses the
challenges and solutions of the optical design, and recent specification updates, as well as a brief comparison between
the prototype and the latest design. However, the emphasis of this paper is the progress of the grism prototype: the
fabrication and test of the complicated diffractive optical elements and powered prism, as well as grism assembly
alignment and testing. Especially how to use different tools and methods, such as IR phase shift and wavelength shift
interferometry, to complete the element and assembly tests. The paper also presents very encouraging results from
recent element tests to assembly tests. Finally we briefly touch the path forward plan to test the spectral characteristic,
such as spectral resolution and response.
KEYWORDS: Mirrors, Telescopes, Optical design, Space telescopes, Staring arrays, Sensors, James Webb Space Telescope, Infrared telescopes, Observatories, Ray tracing
The WFIRST-AFTA Wide-Field Infrared Survey Telescope TMA optical design provides 0.28-sq°FOV Wide Field Channel at 0.11” pixel scale, operating at wavelengths between 0.76-2.0μm, including a spectrograph mode (1.35-1.95μm.) An Integral Field Channel provides a discrete 3”x3.15” field at 0.15” sampling.
We present the Wide Field Infra-Red Survey Telescope (WFIRST) wide field instrument concept based on the reuse of a
2.4m telescope recently made available to NASA. Two instrument channels are described, a wide field channel
(~0.8x0.4degrees, 300Mpix, imaging and spectroscopy over 0.76-2.0um), and an integral field unit (3x3 arcsec, 1Mpix,
R{2pixel} ~100 over 0.6-2.0um). For this mission concept, the telescope, instruments, and spacecraft are in a
geosynchronous orbit and are designed for serviceability. This instrument can accomplish not only the baseline exoplanet
microlensing, dark energy, and infrared surveys for WFIRST, but can perform at higher angular resolution and with
deeper observations. This enables significant opportunities for more capable general observer programs. The emphasis
on achieving very good imaging stability is maintained from the previous work.
The SAFIRE, the Submillimeter and Far InfraRed Experiment, was designed for interstellar physics in the airborne
Observatory SOFIA. SAFIRE is a cryogenic Echelle Grating spectrograph for covering 27 to 470 microns, with R
ranging from 2-6,000. Here we will discuss the details of the optical design, the design process, and the performance of
the instrument.
Following up on Cassini/CIRS, we are building the next-generation Composite InfraRed Spectrometer for deep-space
planetary exploration. CIRS-Lite combines Mid & Far-IR channels into a single instrument with 4x the spectral
sensitivity of CIRS. Here we discuss the instrument optical design, the design process, and the system performance.
The ATALST (Advanced Technology for Large Aperture Space Telescopes) effort has presented several design
incarnations. Here we will discus the design process in detail and compare the design and performance of the 9.2m
segmented, the 8m monolithic on-axis and 8m x 6m off-axis concepts.
ATLAST-8m is an 8-meter monolithic UV/optical/NIR space observatory which could be placed in orbit at Sun-Earth
L2 by a heavily lift launch vehicle. Two development study cycles have resulted in a detailed concept including a dual
foci optical design; several primary mirror launch support and secondary mirror support structural designs; spacecraft
propulsion, power and pointing control design; and thermal design. ATLAST-8m is designed to yield never before
achieved performance to obtain fundamental astronomical breakthroughs.
We present results of a study of a deployable version of the Advanced Technology Large-Aperture Space Telescope
(ATLAST), designed to operate in a Sun-Earth L2 orbit. The primary mirror of the segmented 9.2-meter aperture has 36
hexagonal 1.315 m (flat-to-flat) glass mirrors. The architecture and folding of the telescope is similar to JWST, allowing
it to fit into the 6.5 m fairing of a modest upgrade to the Delta-IV Heavy version of the Evolved Expendable Launch
Vehicle (EELV). We discuss the overall observatory design, optical design, instruments, stray light, wavefront sensing
and control, pointing and thermal control, and in-space servicing options.
The ATALST (Advanced Technology for Large Aperture Space Telescopes) effort has presented several design
incarnations. Here we will compare the design and performance of the 9.2m segmented, the 8m monolithic on-axis and
8m x 6m off-axis concepts.
We present the latest optical design concepts for the Joint Dark Energy Mission (JDEM). This mission will tightly
constrain the cosmological parameters describing the accelerating expansion of the universe. The current candidate
designs are based on extensive examination of the interplay of requirements for the leading techniques being considered
for space borne observation: Baryon Acoustic Oscillation (BAO), Type Ia Supernovae (SN), and gravitational Weak
Lensing (WL). All techniques require very large fields of view across the visible/near infrared spectrum; BAO uniquely
requires a moderate dispersion wide field spectroscopy capability. Weak lensing requires very good stability and
knowledge of the point spread function in order to enable detection of local variations in galaxy ellipticities caused by
the intervening dark matter. SN imaging spectroscopy should be done to high photometric signal to noise in order to
make best use of these 'standard candles.' We have studied medium class and smaller, "Probe" class implementations
enabling from one to three of these techniques. We describe two concepts that were submitted to the 2010 Astrophysics
Decadal review as well as current concepts.
ATLAST-8 is an 8-meter monolithic UV/optical/NIR space observatory to be placed in orbit at Sun-Earth L2 by
NASA's planned Ares V cargo launch vehicle. ATLAST-8 will yield fundamental astronomical breakthroughs. A one
year mission concept study has developed a detailed point design for the optical telescope assembly and spacecraft. The
mission concept assumes two enabling technologies: NASA's planned Ares-V launch vehicle (scheduled for 2019) and
autonomous rendezvous and docking (AR&D). The unprecedented Ares-V payload and mass capacity enables the use
of a massive, monolithic, thin-meniscus primary mirror - similar to a VLT or Subaru. Furthermore, it enables simple
robust design rules to mitigate cost, schedule and performance risk. AR&D enables on-orbit servicing, extending
mission life and enhancing science return.
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.
Two of the GOES instruments, the Imager and the Sounder, perform scans of the Earth to provide a full disc picture of the Earth. To verify the entire scan process, an image of a target that covers an 18o circular field-of-view is collimated and projected into the field of regard of each instrument. The Wide Field Collimator 2 (WFC2) 1 has many advantages over its predecessor, WFC1, including lower thermal dissipation, higher far field MTF, smaller package, and a more intuitive (faster) focusing process. The illumination source is an LED array that emits in a narrow spectral band centered at 689 nm, within the visible spectral bands of the Imager and Sounder. The illumination level can be continuously adjusted electronically. Lower thermal dissipation eliminates the need for forced convection cooling and minimizes time to reach thermal stability. The lens system has been optimized for the illumination source spectral output and athermalized to remain in focus during bulk temperature changes within the laboratory environment. The MTF of the lens is higher than that of the WFC1 at the edge of FOV. The target is focused in three orthogonal motions, controlled by an ergonomic system that saves substantial time and produces a sharper focus.
The GOES Imager and Sounder instruments each observe the full Earth disk, 17.4° in diameter, from geostationary orbit. Pre-launch, each instrument's dynamic scanning performance is tested using the projection of a test pattern from a wide-field collimator. We are fabricating a second wide-field collimator (WFC2) to augment this test program. The WFC2 has several significant advantages over the existing WFC1. The WFC2 target illumination system uses an array of light-emitting diodes (LEDs) radiating at 680nm, which is within the visible bands of both the Imager and Sounder. The light from the LEDs is projected through a non-Lambertian diffuser plate and the target plate to the pupil of the projection lens. The WFC2's power dissipation is much lower than that of WFC1, decreasing stabilization time and eliminating the need for cooling fans. The WFC2's custom-designed 5-element projection lens has the same effective focal length (EFL) as the WFC1 projection lens. The WFC2 lens is optimized for the LED's narrow spectral band simplifying the design and improving image quality. The target plate is mounted in a frame with a mechanized micro-positioner system that controls three degrees of freedom: tip, tilt, and focus. The tip and tilt axes intersect in the WFC's image plane, and all adjustments are controlled remotely by the operator observing the target plate through an auto-collimating telescope.
Several designs of filters for use in vacuum UV imaging systems are discussed. These designs incorporate all reflective optics,and are characterized by comparatively high in-band throughout, very low out-of-band transmission and sub-arcsecond spatial resolution. In addition, they an be tuned over ranges useful for vacuum UV astronomical observations. Results from a simplified laboratory version of the filters intended to prove the concept are presented.
The Composite Infrared Spectrometer (CIRS) is an instrument currently under development at NASA Goddard Space Flight Center for the Cassini mission to Saturn. The CIRS optical design heritage extends back to the Infrared Interferometer Spectrometer (IRIS) which flew on Voyager. CIRS is the next logical step in the exploration of the atmosphere of Saturn and Titan. It will obtain more complete sets of data with broader spectral coverage, higher spectral and spatial resolution, and greater sensitivity. The CIRS optical design consists of four subassemblies: (1) a 50.8 cm diameter Cassegrain telescope, (2) a Mid-Infrared (MIR) Michelson interferometer, (3) a Far-Infrared (FIR) polarizing interferometer, and (4) a Reference interferometer (RI).
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