SPHEREx is a Medium Explorer astrophysics mission that requires a wide-field cryogenic short-wave infrared (SWIR) to mid-wave infrared (MWIR) telescope. The SPHEREx telescope has been designed and built at Ball Aerospace based on a JPL optical prescription and system architecture. The telescope has a 20cm entrance pupil, three freeform aluminum mirrors, a dichroic beam splitter furnished by Caltech, and forms two images in the SWIR and MWIR spectral bands. The “all-aluminum” architecture combined with a cryogenic space environment defines the opto-mechanical design approach for this system. Ball Aerospace performed developmental testing on a flight-like aluminum engineering development mirror for cryogenic surface figure and measured the differential thermal expansion of structural and optical aluminum materials. These development tests validated aspects of the athermal design prior to system-level integration and test. The telescope alignment process uses a laser tracker and system wavefront error (WFE) data to determine the adjustment of two mirrors and a focal plane assembly optical simulator (FPAOS). The FPAOS provides a retroreflection of interferometer light from each image location and an athermal focus position. The FPAOS was used in place of the SWIR band focal plane during system alignment and was moved to the MWIR focal plane interface to validate WFE performance in both bands. A cryogenic system WFE test was conducted to validate SWIR band performance at operational temperatures, and a post-vibrational WFE test demonstrates flight readiness. The SPHEREx telescope has been tested, delivered, and is ready for the next level of system integration.
The James Webb Space Telescope’s (Webb’s) deployable primary and secondary mirrors are actively controlled to achieve and maintain precise optical alignment on-orbit. Each of the 18 primary mirror segment assemblies (PMSAs) and the secondary mirror assembly (SMA) are controlled in six degrees of freedom by using six linear actuators in a hexapod arrangement. In addition, each PMSA contains a seventh actuator that adjusts radius of curvature (RoC). The actuators are of a novel stepper motor-based cryogenic two-stage design that is capable of sub-10 nm motion accuracy over a 20 mm range. The nm-level motion of the 132 actuators were carefully tested and characterized before integration into the mirror assemblies. Using these test results as an initial condition, knowledge of each actuator’s length (and therefore mirror position) has relied on software bookkeeping and configuration control to keep an accurate motor step count from which actuator position can be calculated. These operations have been carefully performed through years of Webb test operations using both ground support actuator control software as well as the flight Mirror Control Software (MCS). While the actuator’s coarse stage length is cross-checked using a linear variable differential transformer (LVDT), no on-board cross-check exists for the nm-level length changes of the actuators’ fine stage. To ensure that the software bookkeeping of motor step count is still accurate after years of testing and to test that the actuator position knowledge was properly handed off from the ground software to the flight MCS, a series of optical tests were devised and performed through the Center of Curvature (CoC) ambient optical test campaigns at the Goddard Space Flight Center (GSFC) and during the thermal-vacuum tests of the entire optical payload that were conducted in Chamber A at Johnson Space Center (JSC). In each test, the actuator Fine Step Count (FSC) value is compared to an external measurement provided by an optical metrology tool with the goal of either confirming the MCS database value, or providing a recommendation for an updated calibration if the measured FSC differs significantly from the MCS-based expectation. During ambient testing of the PMSA hexapods, the nm-level actuator length changes were measured with a custom laser deflectometer by measuring tilts of the PMSA. The PMSA RoC fine stage characterization was performed at JSC using multi-wave interferometric measurements with the CoC Optical Assembly (COCOA). Finally, the SMA hexapod fine stage characterization test was performed at JSC using the NIRCam instrument in the “pass-and-a-half” test configuration using a test source from the Aft-Optics System Source Plate Assembly (ASPA). In this paper, each of these three tests, subsequent data analyses, and uncertainty estimations will be presented. Additionally, a summary of the ensemble state of Webb’s actuator fine stages is provided, along with a comparison to a Wavefront Sensing and Control (WFSC)-based requirement for FSC errors as they relate to the optical alignment convergence of the telescope on-orbit.
KEYWORDS: Mirrors, Point spread functions, Optical alignment, James Webb Space Telescope, Space telescopes, Telescopes, Cryogenics, Monte Carlo methods
The James Webb Space Telescope is a large, deployable telescope that will operate at cryogenic temperatures at the Earth-Sun Lagrange 2 point. The Webb Optical Telescope Element (OTE) consists of 18 actively controlled Primary Mirror Segment Assemblies (PMSAs), an actively controlled Secondary Mirror Assembly (SMA), and an Aft-Optics Subsystem (AOS) that contains a fixed Tertiary Mirror and a Fine Steering Mirror. The OTE is combined with the Integrated Science Instrument Module (ISIM) to create the full optical train called OTIS (OTE and ISIM).
OTIS has recently undergone cryogenic vacuum testing in Chamber A at Johnson Space Center in Houston, TX. A key outcome of this test was to verify there is adequate range of motion in PMSA and SMA actuators to align them to AOS/ISIM under flight-like conditions. The alignment state of the PMSAs and SMA was measured using photogrammetry and cross-checked optically using a variation of a classical Hartmann test. In the “Pass-and-a-Half” (PAAH) configuration, fiber sources near the Cassegrain focus propagate light through the full optical train and small tilts on the PMSAs create an array of spots on the science instrument detectors, mimicking the effect of a Hartmann mask. Comparison of measured and modeled spot arrays provides the alignment state of the SMA and the global tilt of the primary mirror. This paper will discuss the methodology, testing, and analysis performed to measure the alignment state of OTIS using the Hartmann method and verify the primary and secondary mirrors can be successfully aligned on orbit to meet performance requirements.
KEYWORDS: Image segmentation, James Webb Space Telescope, Space telescopes, Wavefronts, Telescopes, Wavefront sensors, Control systems, Mirrors, Image processing, Sensors
A subset of the Wavefront Sensing and Controls (WFSC) operations for JWST were demonstrated during its recent cryo-vac testing using the flight telescope and instruments, and a functional simulation of the spacecraft and ground system. The demonstration had three goals: to confirm the operation of the flight data collection scripts, to check the WFSC optical components, and to verify the coordinates and influence functions that will be used for flight WFSC. In this paper, we present the results and lessons learned from this demonstration.
The James Webb Space Telescope (JWST) Optical Telescope Element (OTE) and Integrated Science Instrument Module (ISIM) completed their element level integration and test programs and were integrated to the next level of assembly called OTE/ISIM (OTIS) at Goddard Space Flight Center (GSFC) in Greenbelt, Maryland in 2016. Before shipping the OTIS to Johnson Space Center (JSC) for optical test at cryogenic temperature a series of vibration and acoustic tests were performed. To help ensure that the OTIS was ready to be shipped to JSC an optical center of curvature (CoC) test was performed to measure changes in the mirror’s optical performance to verify that the telescope’s primary mirror was not adversely impacted by the environmental testing and also help us in understanding potential anomalies identified during the JSC tests. The 6.5 meter diameter primary mirror consists of 18 individual hexagonal segments. Each segment is an off-axis asphere. There are a total of three prescriptions repeated six times each. As part of the CoC test each segment was individually measured using a high-speed interferometer (HSI) designed and built specifically for this test. This interferometer is capable of characterizing both static and dynamic characteristics of the mirrors. The latter capability was used, with the aid of a vibration stinger applying a low-level input force, to measure the dynamic characteristic changes of the PM backplane structure. This paper describes the CoC test setup and both static and dynamic test results.
The James Webb Space Telescope (JWST) telescope’s Secondary Mirror Assembly (SMA) and eighteen Primary Mirror Segment Assemblies (PMSAs) are each actively controlled in rigid body position via six hexapod actuators. Each of the PMSAs additionally has a radius of curvature actuator. The mirrors are stowed to the mirror support structure to survive the launch environment and then must be deployed 12.5 mm to reach the nominally deployed position before the Wavefront Sensing & Control (WFSC) alignment and phasing process begins. JWST requires testing of the full optical system in a Cryogenic Vacuum (CV) environment before launch. The cryo vacuum test campaign was executed in Chamber A at the Johnson Space Center (JSC) in Houston Texas. The test campaign consisted of an ambient vacuum test, a cooldown test, a cryo stable test at 65 Kelvin, a warmup test, and finally a second ambient vacuum test. Part of that test campaign was the functional and performance testing of the hexapod actuators on the flight mirrors. This paper will describe the testing that was performed on all 132 hexapod and radius of curvature actuators. The test campaign first tests actuators individually then tested how the actuators perform in the hexapod system. Telemetry from flight sensors on the actuators and measurements from external metrology devices such as interferometers, photogrammetry systems and image analysis was used to demonstrate the performance of the JWST actuators. The mirror move commanding process was exercised extensively during the JSC CV test and many examples of accurately commanded moves occurred. The PMSA and SMA actuators performed extremely well during the JSC CV test, and we have demonstrated that the actuators are fully functional both at ambient and cryo temperatures and that the mirrors will go to their commanded positions with the accuracy needed to phase and align the telescope.
KEYWORDS: Adaptive optics, Mirrors, James Webb Space Telescope, Cryogenics, Telescopes, Optical alignment, Space telescopes, Photogrammetry, Monte Carlo methods, Actuators
The James Webb Space Telescope is a large space-based astronomical telescope that will operate at cryogenic temperatures. Because of its size, the telescope must be stowed in an inoperable configuration for launch and remotely reconfigured in space to meet the operational requirements using active Wave Front Sensing and Control (WFSC). Predicting optical performance for the flight system relies on a sequence of incremental tests and analyses that has culminated with the cryogenic vacuum test of the integrated Optical Telescope Element (OTE) and Integrated Science Instrument Module (ISIM) referred to as OTIS. The interplay between the optical budgeting process, test verification results at incrementally increasing levels of integration, use of test validated models, and the WFSC process to produce the final optical performance predictions for final verification by analysis will be presented.
The James Webb Space Telescope (JWST) recently saw the completion of the assembly process for the Optical Telescope Element and Integrated Science Instrument Module (OTIS). This integration effort was performed at Goddard Space Flight Center (GSFC) in Greenbelt, Maryland. In conjunction with this assembly process a series of vibration and acoustic tests were performed. To help assure the telescope’s primary mirror was not adversely impacted by this environmental testing an optical center of curvature (CoC) test was performed to measure changes in the mirror’s optical performance. The primary is a 6.5 meter diameter mirror consisting of 18 individual hexagonal segments. Each segment is an off-axis asphere. There are a total of three prescriptions repeated six times each. As part of the CoC test each segment was individually measured using a high-speed interferometer (HSI) designed and built specifically for this test. This interferometer is capable of characterizing both static and dynamic characteristics of the mirrors. The latter capability was used, with the aid of a vibration stinger applying a low-level input force, to measure the dynamic characteristic changes of the PM backplane structure. This paper describes the CoC test setup, an innovative alignment method, and both static and dynamic test results.
The James Webb Space Telescope's (JWST) end-to-end optical system will be tested in a cryogenic vacuum
environment before launch at NASA Johnson Space Center’s (JSC) Apollo-era, historic Chamber A thermal
vacuum facility. During recent pre-test runs with a prototype “Pathfinder” telescope, the vibration in this
environment was found to be challenging for the baseline test approach, which uses phase retrieval of images
created by three sub-apertures of the telescope. To address the vibration, an alternate strategy implemented using
classic Hartmann test principles combined with precise mirror mechanisms to provide a testing approach that is
insensitive to the dynamics environment of the chamber. The measurements and sensitivities of the Hartmann
approach are similar to those using phase retrieval over the original sparse aperture test. The Hartmann test
concepts have been implemented on the JWST Test Bed Telescope, which provided the rationale and empirical
evidence indicating that this Hartmann style approach would be valuable in supplementing the baseline test
approach.
This paper presents a Hartmann approach implemented during the recent Pathfinder test along with the test
approach that is currently being considered for the full optical system test of JWST. Comparisons are made
between the baseline phase retrieval approach and the Hartmann approach in addition to demonstrating how the
two test methodologies support each other to reduce risk during the JWST full optical system test.
The James Webb Space Telescope (JWST) project is an international collaboration led by NASA’s Goddard Space
Flight Center (GSFC) in Greenbelt, MD. JWST is NASA’s flagship observatory that will operate nearly a million miles
away from Earth at the L2 Lagrange point. JWST’s optical design is a three-mirror anastigmat with four main optical
components; 1) the eighteen Primary Mirror Segment Assemblies (PMSA), 2) a single Secondary Mirror Assembly
(SMA), 3) an Aft-Optics Subsystem (AOS) consisting of a Tertiary Mirror and Fine Steering Mirror, and 4) an
Integrated Science Instrument Module consisting of the various instruments for JWST. JWST’s optical system has been
designed to accommodate a significant amount of alignment capability and risk with the PMSAs and SMA having rigid
body motion available on-orbit just for alignment purposes. However, the Aft-Optics Subsystem (AOS) and Integrated
Science Instrument Module (ISIM) are essentially fixed optical subsystems within JWST, and therefore the cryogenic
alignment of the AOS to the ISIM is critical to the optical performance and mission success of JWST.
In support of this cryogenic alignment of the AOS to ISIM, an array of fiber optic sources, known as the AOS Source
Plate Assembly (ASPA), are placed near the intermediate image location of JWST (between the secondary and tertiary
mirrors) during thermal vacuum ground-test operations. The AOS produces images of the ASPA fiber optic sources at
the JWST focal surface location, where they are captured by the various science instruments. In this manner, the AOS
provides an optical yardstick by which the instruments within ISIM can evaluate their relative positions to and the
alignment of the AOS to ISIM can be quantified. However, since the ASPA is located at the intermediate image location
of the JWST three-mirror anastigmat design, the images of these fiber optic sources produced by the AOS are highly
aberrated with approximately 2-3μm RMS wavefront error consisting mostly of 3rd-order astigmatism and coma. This is
because the elliptical tertiary mirror of the AOS is used off of its ideal foci locations without the compensating
wavefront effects of the JWST primary and secondary mirrors. Therefore, the PSFs created are highly asymmetric with
relatively complex structure and the centroid and encircled energy analyses traditionally used to locate images are not
sufficient for ensuring the AOS to ISIM alignment.
A novel approach combining phase retrieval and spatial metrology was developed to both locate the images with respect
to the AOS and provide calibration information for eventual AOS to ISIM alignment verification. During final JWST
OTE and ISIM (OTIS) testing, only a single thru-focus image will be collected by the instruments. Therefore, tools and
processes were developed to perform single-image phase retrieval on these highly aberrated images such that any single
image of the ASPA source can provide calibrated knowledge of the instruments’ position relative to the AOS. This paper
discusses the results of the methodology, hardware, and calibration performed to ensure that the AOS and ISIM are
aligned within their respective tolerances at JWST OTIS testing.
The performance of an optical system is best characterized by either the point spread function (PSF) or the optical
transfer function (OTF). However, for system budgeting purposes, it is convenient to use a single scalar metric, or a
combination of a few scalar metrics to track performance. For the James Webb Space Telescope, the Observatory
level requirements were expressed in metrics of Strehl Ratio, and Encircled Energy. These in turn were converted to
the metrics of total rms WFE and rms WFE within spatial frequency domains. The 18 individual mirror segments
for the primary mirror segment assemblies (PMSA), the secondary mirror (SM), tertiary mirror (TM), and Fine
Steering Mirror have all been fabricated. They are polished beryllium mirrors with a protected gold reflective
coating. The statistical analysis of the resulting Surface Figure Error of these mirrors has been analyzed. The
average spatial frequency distribution and the mirror-to-mirror consistency of the spatial frequency distribution are
reported. The results provide insight to system budgeting processes for similar optical systems.
The James Webb Space Telescope (JWST) Secondary Mirror Assembly (SMA) is a circular 740mm diameter beryllium convex hyperboloid that has a 23.5nm-RMS (λ/27 RMS) on-orbit surface figure error requirement. The radius of curvature of the SMA is 1778.913mm±0.45mm and has a conic constant of -1.6598±0.0005. The on-orbit operating
temperature of the JWST SMA is 22.5K. Ball Aerospace & Technologies Corp. (BATC) is under contract to Northrop Grumman Aerospace Systems (NGAS) to fabricate, assemble, and test the JWST SMA to its on-orbit requirements including the optical testing of the SMA at its cryogenic operating temperature. BATC has fabricated and tested an
Aspheric Test Plate Lens (ATPL) that is an 870mm diameter fused silica lens used as the Fizeau optical reference in the ambient and cryogenic optical testing of the JWST Secondary Mirror Assembly (SMA). As the optical reference for the SMA optical test, the concave optical surface of the ATPL is required to be verified at the same 20K temperature range required for the SMA. In order to meet this objective, a state-of-the-art helium cryogenic testing facility was developed to support the optical testing requirements of a number of the JWST optical testing needs, including the ATPL and SMA. With the implementation of this cryogenic testing facility, the ATPL was successfully cryogenically tested and performed to less than 10nm-RMS (λ/63 RMS) surface figure uncertainty levels for proper reference backout during the SMA optical testing program.
The James Webb Space Telescope (JWST) Primary Mirror Segment Assembly (PMSA) was required to meet NASA
Technology Readiness Level (TRL) 06 requirements in the summer of 2006. These TRL06 requirements included
verifying all mirror technology systems level readiness in simulated end-to-end operating conditions. In order to support
the aggressive development and technology readiness schedule for the JWST Primary Mirror Segment Assembly
(PMSA), a novel approach was implemented to verify the nanometer surface figure distortion effects on an in-process
non-polished beryllium mirror surface. At the time that the TRL06 requirements needed to be met, a polished mirror
segment had not yet been produced that could have utilized the baselined interferometric optical test station. The only
JWST mirror segment available was a finished machined segment with an acid-etched optical surface. Therefore an
Electronic Speckle Pattern Interferometer (ESPI) was used in coordination with additional metrology techniques to
perform interferometric level optical testing on a non-optical surface. An accelerated, rigorous certification program was
quickly developed for the ESPI to be used with the unfinished optical surface of the primary mirror segment. The ESPI
was quickly implemented into the PMSA test program and optical testing was very successful in quantifying the
nanometer level surface figure deformation changes in the PMSA due to assembly, thermal cycling, vibration, and
acoustic testing. As a result of the successful testing, the PMSA passed all NASA TRL06 readiness requirements.
The James Webb Space Telescope (JWST) is an on axis three mirror anastigmat telescope with a primary mirror, a
secondary mirror, and a tertiary mirror. The JWST mirrors are constructed from lightweight beryllium substrates and the
primary mirror consists of 18 hexagonal mirror segments each approximately 1.5 meters point to point. Ball Aerospace
and Technologies Corporation leads the mirror manufacturing team and the team utilizes facilities at six locations across
the United States. The fabrication process for each individual mirror assembly takes approximately six years due to
limitations dealing with the number of segments and manufacturing & test facilities. The primary mirror Engineering
Development Unit (EDU) recently completed the manufacturing process with the final cryogenic performance test of the
mirror segment assembly. The 18 flight primary mirrors segments, the secondary mirror, and the tertiary mirror are all
advanced in the mirror production process with many segments through the final polishing process, coating process, final
assembly, vibration testing, and final acceptance testing. Presented here is a status of the progress through the
manufacturing process for all of the flight mirrors.
The James Webb Space Telescope (JWST) is a large space based astronomical telescope that will operate at
cryogenic temperatures. The telescope by virtue of its size must be stowed in an inoperable configuration for launch
and remotely reconfigured in space to meet the operational requirements using active Wave Front Sensing and
Control (WFSC). This paper will report on the optical budgeting process used to manage the performance of the
active system. The current status of the design and verification of the optical hardware, the WFSC processes, and
the total system verification modeling will be presented. More detailed discussions of the system verification by
analysis will be presented in separate accompanying papers.
JWST optical component in-process optical testing and cryogenic requirement compliance certification, verification &
validation is probably the most difficult metrology job of our generation in astronomical optics. But, the challenge has
been met: by the hard work of dozens of optical metrologists; the development and qualification of multiple custom test
setups; and several new inventions, including 4D PhaseCam and Leica Absolute Distance Meter. This paper summarizes
the metrology tools, test setups and processes used to characterize the JWST optical components.
The James Webb Space Telescope (JWST) Secondary Mirror (SM) is a 738 mm edge-diameter convex hyperbola that will be operating at 30K. Due to JWST’s science and technical requirements, the requirements on the SM are relatively tight. Therefore highly accurate, rigorous cryogenic testing of the surface figure as well as the prescription is required. The optical testing of a convex mirror of this size has not been performed before at cryogenic temperatures. This paper discusses the testing approaches and configurations that are under consideration at Ball Aerospace & Technologies Corp. (BATC) for testing the JWST SM at cryogenic temperatures.
The ability to grind and polish steep aspheric surfaces to high quality is limited by the tools used for working the surface. The optician prefers to use large, stiff tools to get good natural smoothing, avoiding small scale surface errors. This is difficult for steep aspheres because the tools must have sufficient compliance to fit the aspheric surface, yet we wish the tools to be stiff so they wear down high regions on the surface. This paper presents a toolkit for designing optimal tools that provide large scale compliance to fit the aspheric surface, yet maintain small scale stiffness for efficient polishing.
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