The Nancy Grace Roman Telescope (RST) is a NASA observatory designed to unravel the secrets of dark energy and dark matter, search for and image exoplanets, and explore many topics in infrared optics. Scheduled to launch in no earlier than October 2026, this 2.4 meter aperture telescope has a field of view 100 times greater than the Hubble Space Telescope. The mission is currently in its construction phase, where integrated modeling between thermal, structural, and optical models of the observatory is necessary to demonstrate science quality images over the range of operational parameters. This presentation discusses the most recent integrated modeling analysis cycle for Roman, including model correlation with our instrument level testing. We include a discussion on improved processes of the handling of the various flows of data between the modeling disciplines and discipline specific monte-carlo analysis predictions. We will finish with the predicted uncertainties and expected performance for our upcoming observatory alignment verification test using machine learning algorithms.
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.
The Roman Space Telescope Grism and Prism assemblies will allow the wide-field instrument (WFI) to perform slitless, multi-object spectroscopy across the complete field of view. These optical elements play a critical role in the High Latitude Wide Area and High Latitude Time Domain Surveys, which are designed to produce robust spectroscopic redshifts for millions of objects over the mission lifetime. To facilitate the characterization of these assemblies, a dedicated test bed was designed and utilized to perform a wide variety of spectroscopic measurements over the full range of operational wavelengths and field angles. Characterized features include, but are not limited to dispersion magnitude, dispersion clocking, encircled energy, total throughput, and bandpass edges. We present the results of this experimental campaign in which the Grism and Prism assemblies met or exceeded many of their design requirements and discuss measurement limitations.
KEYWORDS: Prisms, Calibration, Polarizers, Polarization, Spectroscopes, Spectral resolution, Equipment, Target detection, Space telescopes, Signal to noise ratio
The Nancy Grace Roman Space Telescope Coronagraph Instrument (CGI) will demonstrate spectroscopy of planets and polarization measurements of disks. The spectroscopy and polarization modes utilize Amici and Wollaston prism designs. The spectroscopy mode, designed and built and Goddard Space Flight Center (GSFC), has a resolution of R50 in 15% bands centered at 660nm and 730nm. The Wollaston design and optics are contributed by the Japanese Aerospace Exploration Agency, with final alignment and testing at GSFC. We present the requirements, ground-to-orbit calibration, and deployable slit operations. We also detail on the design, results from the as-built flight assemblies.
The Nancy Grace Roman Space Telescope (“Roman”) was prioritized by the 2010 Decadal Survey in Astronomy & Astrophysics and is NASA’s next flagship observatory. Launching no earlier than 2026, Roman will explore the nature of dark energy, as well as expand the census of exoplanets in our galaxy via microlensing. Roman will also demonstrate key technology needed to image and spectrally characterize extra-solar planets. Roman’s large field of view, agile survey capabilities, and excellent stability enable these scientific objectives, yet present unique challenges for the design, test, and verification of its optical system. The Roman optical system comprises an optical telescope assembly (OTA) and two instruments: the primary science wide-field instrument (WFI) and a technology demonstration coronagraph instrument (CGI), and the instrument carrier (IC), which meters the OTA to each instrument. This paper presents a status of the optical system hardware as it begins integration and test (I&T), as well as describes key optical test, alignment, and verification activities as part of the I&T program.
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.
The LRCTF (Laser Ranging Characterization and Test Facility) is a unique facility built at NASA GSFC to provide thermal-optical testing of the next generation GPS LRA (Global Positioning Satellite’s Laser Retroreflector Array) laser ranging target. The 400mm diameter target is an array consisting of 48 total internal reflection retroreflectors and has an optical cross section requirement of 100 MSM (million square meters). To verify that the array meets this requirement during on-orbit conditions, the LRCTF is equipped with a 400mm test beam, a data product output consisting of full aperture FFDPs (Far Field Diffraction Patterns) and a thermal chamber. The FFDPs are used to calculate the OCS. This paper will describe the facility design, alignment approach, and verification process.
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.
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.
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.
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.
Pinhole is a critical device in single photon confocal microscopy (SPCM) owning to its ability to block the background
noise scattered from back and forth of the focal plane. Without pinhole, the sectioning ability of SPCM will be degraded
and many background noise signals will occurred together with useful signals, and sometimes these bad noises can
submerge the details that we are interested in. However a pinhole with too small diameter will block both background
noises and part of signals and decrease the intensity of the image. Therefore in many cases pinhole size should be
selected carefully. Unfortunately because of constrains in mechanics, a pinhole that can change its size continuously, for
example from 10 μm to 100 μm, is unavailable. For most commercial confocal microscopies, only several discrete
pinhole sizes are provided, such as 10 μm, 30 μm, 60 μm etc. Things will be even harder for some imaging systems
which use the input interface of a single mode fiber as the pinhole of SPCM, and then the pinhole size of these systems
will be fixed, which far limit the optimization of systems’ performance.
In this paper, we design a size-variable pinhole setup that can offer a virtual pinhole with its diameter adjustable, which
includes a physical pinhole (or single mode fiber) and a fine designed zoom relay (ZR) optical system. The
magnification ratio of this ZR can vary smoothly while keeping the conjugation distance unchanged. The aberrations of
the ZR are well balanced and diffraction-limited image performance are obtained so that the virtual pinhole can block
background scattering noise and pass the in-focus signal effectively and accurately. Simulation results are also provided
and discussed.
In recent development of fluorescence microscopy, the out-of-focus fluorescence background that arises when imaging
deep inside biological tissues is critical in determining the image quality and penetration depth. Focal modulation
microscopy (FMM) is an advanced fluorescence technique that can provide high subcellular resolution when imaging
thick specimens mainly by preserving the signal-to-background ratio.
In the performance evaluation of phase-shifting interferometers for figure metrology, the height response, or height transfer function, is rarely taken into consideration, because in most applications smooth surfaces are measured and only the lowest spatial frequencies are of interest. For measurements with low uncertainty it is important to understand the height response as a function of the spatial-frequency content of a surface under test, in particular when it contains form-error components with frequencies at the high end of an interferometer's spatial-frequency passband. A mirror with a patterned area of 140-mm diameter, consisting of several subpatterns with varying spatial frequency, was used to evaluate the spectral response. Our goal was to develop a method for efficient mapping of the spectral response over the circular field of view of a phase-shifting interferometer. A new way of representing the dependence of the spectral response on the field of view of an interferometer is described.
We describe a glancing-incidence interferometric double-pass test, based on a pair of computer-generated holograms
(CGHs), for mandrels used to fabricate x-ray mirrors for space-based x-ray telescopes. The design of the test and its
realization are described. The application illustrates the advantage of dual-CGH tests for the complete metrology of precise
optical surfaces.
A glancing-incidence interferometric test for large x-ray mirror mandrels, using two computer-generated holograms (CGHs), is described. The two CGHs are used to form a double-pass glancing-incidence system. One layout of the CGH-cavity glancing-incidence interferometer is studied and factors relating to its design are analyzed. A semianalytical expression for the phase function is derived that avoids high-order ripple errors and improves the efficiency of the CGH pattern generation. A system of coarse and fine fiducials for establishing the CGH-cavity and aligning the tested mandrel is discussed. Compared with traditional measurement devices, such as coordinate measuring machines (CMMs) or other scanning metrology systems, the CGH-cavity glancing-incidence interferometer can measure a mandrel surface without mechanical contact, at a high spatial sampling frequency, with lower uncertainty, and at high speed.
In characterizing the performance of a phase-shifting interferometer, the dependence of the measured height on the
spatial frequency is rarely considered. We describe a test mirror with a special height relief that can be used to measure
the height transfer function for the interferometer in a fashion analogous to the measurement of the modulation transfer
function for the optical imaging system. We fabricated the test mirror at the National Institute of Standards and
Technology (NIST) using a lithography-based process. The test mirror has several patterns (reminiscent of moth
antennae) with variable spacing in radial direction. We describe the fabrication of the test mirror and its application to
test the performance of the interferometer.
An important factor influencing the image quality of space or military optical systems is that the broad environmental temperature ranges. It would bring some problems on design, fabrication and mounting of the optical system. The ways of getting rid of the problems and improving the image quality of optical systems by using aspherical metal mirrors to the infrared thermal imaging system are presented in this paper. The choice of mirrors materials, the design of mirrors structure, the analysis of factors of influencing mirrors surface figure are discussed. The actual optical system designed in this paper is a Cassegrain objective, and the reflective surfaces of the primary mirror and secondary mirror are conicoid surfaces. The diameter of the primary mirror is φ240mm, the materials of mirrors is aluminum alloys, and the mounting structure is flexible. The aspherical surface of the metal mirror are fabricated by precision diamond turning machine, and the error of the surface figure is less than 0.5μm. The results of the battlefield test show that the infrared system with metal mirrors discussed in this paper has met the optical design specifications.
Polarization aberration is one of the most important factors affecting the performance of optical systems, especially in systems which have many reflectors. The polarization response characters of the reflectors will change the polarization state of the incident light and the polarization aberration will affect the imaging quality of the system. In many resource satellites R-C reflective systems are often used in primary optical systems. The main elements of the R-C reflective systems are reflectors coated with thin films, so polarization aberration must be controlled to improve the imaging quality of the systems. In this paper ZEMAX software is used to realize the simulation of the optical system of a resource satellite and polarization analysis of the system is presented. According to the results of the polarization analysis, the whole optical system is optimized and the ways to control the polarization aberration are summarized. As a result of the study, a conclusion can be drawn that polarization is an important aspect in optical design. To achieve good imaging quality, polarization aberration must be controlled very well, moreover, optical thin film design should be considered while designing optical systems.
In order to get a simple LED illumination system with a short length, the LED needs a large irradiant angle (2ω = 90°) and the lens needs a large aperture. This would conduce a severe non-uniformity on the illuminated area and a very low F-number. So it is rather difficult to design a singlet lens for LED illumination system with a better uniformity in certain area because of the non-uniform irradiation of the LED and the contradiction between the focal length and the aperture. For an on-axial point source, the spherical aberrations in different apertures can change the propagating direction of the rays; therefore it is possible to get a uniform illumination with the help of spherical aberrations. Light density function on the illuminated plan is deduced, and the merit function for uniform illumination in certain area is defined in this paper. By using the optical design software ZEMAX EE, the search of the optimal value for the given focal length is done. The computer simulation results show that by producing spherical aberrations correctly a better uniformity illumination can be obtained on the illuminated area in certain distance successfully.
In order to measure the vibrant track of a cable crossing a river, a complex optical system is introduced to realize the image of a rectangle on a CCD image surface. The quantitative diagnosis of the system's aberrations reveals that the distortion is beyond the tolerance. A new and accurate method of digital correcting the distortion with asymmetrical distribution is proposed.
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