The James Webb Space Telescope (JWST) primary mirror (PM) is 6.6 m in diameter and consists of 18 hexagonal segments, each 1.5 m point-to-point. Each segment has a 6 degree-of-freedom hexapod actuation system and a radius-of-curvature (ROC) actuation system. The full telescope was tested at its cryogenic operating temperature at Johnson Space Center (JSC) in 2017. This testing included center-of-curvature measurements of the PM wavefront error using the Center-of-Curvature Optical Assembly (COCOA), along with the Absolute Distance Meter Assembly (ADMA). The COCOA included an interferometer, a reflective null, an interferometer-null calibration system, coarse and fine alignment systems, and two displacement measuring interferometer systems. A multiple-wavelength interferometer was used to enable alignment and phasing of the PM segments. By combining measurements at two laser wavelengths, synthetic wavelengths up to 15 mm could be achieved, allowing mirror segments with millimeter-level piston errors to be phased to the nanometer level. The ADMA was used to measure and set the spacing between the PM and the focus of the COCOA null (i.e., the PM center-of-curvature) for determination of the ROC. This paper describes the COCOA, the PM test setup, the testing performed, the test results, and the performance of the COCOA in aligning and phasing the PM segments and measuring the final PM wavefront error.
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) 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.
KEYWORDS: Mirrors, James Webb Space Telescope, Cryogenics, Interferometers, Space telescopes, Mirrors, James Webb Space Telescope, Cryogenics, Space telescopes, Image segmentation, Wavefronts, Optical fabrication, Aerospace engineering, Telescopes
The James Webb Space Telescope (JWST) Optical Telescope Element (OTE) consists of a 6.6 m clear aperture, 18
segment primary mirror, all-reflective, three-mirror anastigmat operating at cryogenic temperatures. To verify
performance of the primary mirror, a full aperture center of curvature optical null test is performed under cryogenic
conditions in Chamber A at the National Aeronautics and Space Administration (NASA) Johnson Space Center (JSC)
using an instantaneous phase measuring interferometer. After phasing the mirrors during the JWST Pathfinder
testing, the interferometer is utilized to characterize the mirror relative piston and tilt dynamics under different facility
configurations. The correlation between the motions seen on detectors at the focal plane and the interferometer validates
the use of the interferometer for dynamic investigations. The success of planned test hardware improvements will be
characterized by the multi-wavelength interferometer (MWIF) at the Center of Curvature Optical Assembly (CoCOA).
The James Webb Space Telescope (JWST) primary mirror (PM) is 6.6 m in diameter and consists of 18 hexagonal segments, each 1.5 m point-to-point. Each segment has a six degree-of-freedom hexapod actuation system and a radius of-curvature (RoC) actuation system. The full telescope will be tested at its cryogenic operating temperature at Johnson Space Center. This testing will include center-of-curvature measurements of the PM, using the Center-of-Curvature Optical Assembly (COCOA) and the Absolute Distance Meter Assembly (ADMA). The COCOA includes an interferometer, a reflective null, an interferometer-null calibration system, coarse and fine alignment systems, and two displacement measuring interferometer systems. A multiple-wavelength interferometer (MWIF) is used for alignment and phasing of the PM segments. The ADMA is used to measure, and set, the spacing between the PM and the focus of the COCOA null (i.e. the PM center-of-curvature) for determination of the ROC. The performance of these metrology systems was assessed during two cryogenic tests at JSC. This testing was performed using the JWST Pathfinder telescope, consisting mostly of engineering development and spare hardware. The Pathfinder PM consists of two spare segments. These tests provided the opportunity to assess how well the center-of-curvature optical metrology hardware, along with the software and procedures, performed using real JWST telescope hardware. This paper will describe the test setup, the testing performed, and the resulting metrology system performance. The knowledge gained and the lessons learned during this testing will be of great benefit to the accurate and efficient cryogenic testing of the JWST flight telescope.
KEYWORDS: Mirrors, Space telescopes, Computer generated holography, James Webb Space Telescope, Telescopes, Interferometers, Monochromatic aberrations, Neodymium, Metrology, Data acquisition
James Webb Space Telescope Optical Telescope Element (OTE) is a three mirror anastigmat consisting of a 6.5 m primary mirror (PM), a secondary mirror (SM) and a tertiary mirror. The primary mirror is made out of 18 segments. The telescope and instruments will be assembled at Goddard Space Flight Center (GSFC) to build the Optical Telescope Element-Integrated Science Instrument Module (OTIS). The OTIS will go through environmental testing at GSFC before being transported to Johnson Space Center for testing at cryogenic temperature. The objective of the primary mirror Center of Curvature test (CoC) is to characterize the PM before and after the environmental testing for workmanship. This paper discusses the CoC test including both a surface figure test and a new method for characterizing the state of the primary mirror using high speed dynamics interferometry.
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) primary mirror is 6.6 m in diameter and consists of 18 hexagonal mirror segments each approximately 1.5 m point-to-point. Each primary mirror segment assembly (PMSA) is constructed from a lightweight beryllium substrate with both a radius-of-curvature actuation system and a six degree-of-freedom hexapod actuation system. With the JWST being a near to mid-infrared observatory, the nominal operational temperature of a
PMSA is 45 K. Each PMSA must be optically tested at 45 K twice, first to measure the change in the surface figure & radius-of-curvature between ambient & cryogenic temperatures and then to verify performance at cryo following final polishing. This testing is conducted at Marshall Space Flight Center's (MSFC's) X-Ray & Cryogenic Facility (XRCF). The chamber & metrology system can accommodate up to six PMSAs per cryo test. This paper will describe the optical metrology system used during PMSA cryogenic testing. This system evolved from systems used during the JWST mirror technology development program. The main components include a high-speed interferometer, a computer-generated holographic null, an absolute distance meter, a tiltable window, and an imaging system for alignment. The optical metrology system is used to measure surface figure error, radius-of-curvature, conic constant, prescription
alignment, clear aperture, and the range & resolution of the PMSA actuation systems.
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 JWST (James Webb Space Telescope) primary mirror consists of 18 hexagonal mirror segments each approximately
1.5 meters point to point. The mirror segments are constructed from a lightweight beryllium substrate with both a
radius-of-curvature actuation system and a six degree-of-freedom hexapod actuation system. The manufacturing process
for each individual mirror assembly takes approximately six years due to limitations dealing with the number of
segments and manufacturing & test facilities. In order to catch any manufacturing or technology roadblocks, as well as
to streamline specific processes, an Engineering Development Unit (EDU) was built to lead the mirror manufacturing
flow. This development unit has all of the same requirements as the flight units and is actually considered to be one of
the flight spare mirrors. The EDU was manufactured with a lead time of approximately six months over the other mirrors
to assure adequate time to optimize each step in the manufacturing process. Manufacturing and tests occurred at six
locations across the U.S. with multiple trips between each. The EDU recently completed this arduous process with the
final cryogenic performance test of the mirror assembly taking place at Marshall Space Flight Center's (MSFC) X-Ray
& Cryogenic Facility (XRCF). Testing included survivability tests to 25 Kelvin, hexapod & radius-of-curvature
actuation systems testing, and cryogenic figure & prescription testing. Presented here is a summary of the tests
performed along with the results of that testing.
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.
James Webb Space Telescope (JWST) has a segmented Primary Mirror (PM). PM is made of 18 beryllium hexagonal shaped segments. Flat-to-flat dimension of a segment is 1.315 meters. The PM is an ellipsoid of~ 6.5 meters in diameter with a conic constant of -0.99666 and a radius of curvature ~16 meters. After the PM, telescope are assembled and instruments are installed the observatory will go through environmental testing. The environmental test consist of acoustic and vibration test. The objective is to measure the change in the surface astigmatism of the Primary mirror segments at center of curvature before and after vibration and acoustic test. At the final stage of assembly the inner segments of the PM have no external fiducials. The challenge is to separate the alignment astigmatism from surface astigmatism without any external fiducials. This paper describes an alignment method that uses the print-through in the mirror segments as fiducials to separate the two astigmatisms.
The JWST (James Webb Space Telescope) primary mirror consists of 18 hexagonal mirror segments. Each segment is approximately 1.5 meters point to point and is constructed from a lightweight beryllium substrate. In order for the 18 segments to act as a single 6.5 meter diameter mirror each one must be capable of 6 degrees of freedom motion relative to the mirror backplane and be able to change its radius of curvature to closely match those of the other segments. As it would be nearly impossible to manufacture the 18 individual
segments with the same radius, a RoC (radius of curvature) actuation mechanism is attached to each mirror allowing RoC fine tuning post manufacturing. The RoC actuation system consists of a single actuator and six struts attached to the back of the mirror. The radius of curvature is matched by closely manufacturing the
radius of each segment relative to the nominal value and then, during cryogenic testing, actuating the RoC of each mirror. This cryogenic actuation reduces polishing times and allows for compensation of radius changes measured during other manufacturing steps. Presented here is a high-level overview of the method used to
set the mirror's radius of curvature at cryogenic temperature, disassemble the mirror system for additional polishing and processing, and perform final cryogenic verification.
Tinsley, under JWST funding, has led the team that has developed a novel and highly versatile piece of ground support equipment for optical surface testing of JWST beryllium mirror segments during optical fabrication. The infrared Scanning Shack Hartmann System (SSHS) offers the advantage of being able to characterize mid-to-high spatial frequency structure on a mirror from early stages of fabrication when slopes may be high and surface irregular, eliminating the need for an extra polishing step before metrology. Working at 9.3μm, the system will accept and measure a wide dynamic range of surface characteristics, including roll-off near the edge of the segment. Knowledge of these surface features at the early grinding stage is imperative if characteristics such as mirror edge roll-off are to be minimized. WaveFront Sciences, producer of commercial COAS and Columbus Shack Hartmann systems, has provided systems engineering and component support for the SSHS system.
The SSHS system is based around a special Long Wave Infrared (LWIR) wavefront sensor developed by WaveFront Sciences that is scanned over the mirror surface, making sub-aperture measurements. The smaller, high-resolution measurements are then stitched together to provide high-resolution measurement of the entire mirror surface, even though the surface is in a rough ground state.
The system leverages technology from smaller visible instrumentation produced by Wavefront Sciences, especially those for surface sub-aperture measurements of semiconductor wafers. This paper will describe the implementation of the first infrared scanning Shack Hartmann system at Tinsley to address optical fabrication optimization of the JWST Primary Mirror Segments.
The context, preparation, and facilitization of Tinsley to produce the 18 JWST primary mirror segments are described,
and an overview of the Project at Tinsley is presented. The mirror segments are aggressively lightweighted,
approximately hexagonal, and approximately 1.32m flat-to-flat. While the optical finishing approach is strongly seated
in Tinsley's Computer Controlled Optical Surfacing (CCOSTM) technology, extensions have been implemented to
address safe and efficient nearly simultaneous flow of the high value mirror segments through numerous cycles of
optical finishing, processing and metrology steps. JWST will operate at cryogenic temperatures, and Tinsley will do
final figuring from a "hit map" made during cryogenic testing at the NASA MSFC X-Ray Calibration Facility (XRCF).
A formal beryllium safety protocol has been established throughout. Extensive handling fixtures assure that the mirrors
are moved from station to station experiencing low accelerations. A rigorous qualification process is applied to each
new fixture, machine and instrument. Special problems of cryo figuring, and co-finishing the segments to stringent
specifications are described.
The 1.4-meter semi-rigid, beryllium Advanced Mirror System Demonstrator (AMSD) mirror completed initial cryogenic testing at Marshall’s X-ray Calibration Facility (XRCF) in August of 2003. Results of this testing show the mirror to have very low cryogenic surface deformation and possess exceptional figure stability. Additionally, the mirror substrate exhibits virtually no change in surface figure over the James Webb Space Telescope (JWST) operational temperature range of 30 to 62 Kelvin. The lightweighted, semi-rigid mirror architecture approach demonstrated here is a precursor to the mirror technology being applied to the JWST observatory. Testing at ambient and cryogenic temperatures included the radius of curvature actuation system and the rigid body displacement system. These two systems incorporated the use of 4 actuators to allow the mirror to change piston, tilt, and radius of curvature. Presented here are the results of the figure change, alignment change, and radius change as a function of temperature. Also shown will be the actuator influence functions at both ambient and cryogenic temperatures.
The telescope for a Terrestrial Planet Finder (TPF) coronagraph has exceedingly stringent phase and amplitude requirements, especially for the large, monolithic primary mirror (possibly as large as 4 meters by 10 meters). The pertinent derived engineering requirements will be summarized based on a described set of science objectives to simulate solar type stars and their companion earth-size planets. We will also present an optical design for a sub-scale coronagraphic testbed as an essential step in examining the system sensitivities. The major subassemblies of the testbed include: 1) a star/planet simulator that affords variation in contrast, adjustable relative separation and angular orientation and 2) a relay optical system representative of a TPF 3-mirror telescope that allows the imposition of known optical perturbations over the desired wavefront spatial frequencies. We will compare these TPF testbed mirror wavefront requirements with levels recently achieved on the Advanced Mirror System Demonstrator and planned for the James Webb Space Telescope (JWST).
The 1.4-m semi-rigid, beryllium Advanced Mirror System Demonstrator (AMSD) mirror has been lightweighted by over 90% (achieving 10 kg/m2 areal density) and optically ground and polished. The mounting structures have been completed and key attachments integrated prior to final polishing. The displacement actuators have been fabricated and tested at ambient and cryogenic temperatures. The integrated assembly represents an off-axis, aspheric, flight panel of a spaceborne mirror array whose radius of curvature (RoC) can be matched with its companion segments and whose position can be separately phased in a rigid body fashion. The results of the initial ambient testing and the cryogenic test set-up of the mirror assembly will be presented including mirror surface characterization and the correction afforded by radius of curvature actuation. Cryogenic testing at MSFC was completed in August 2003. The lightweighted, semi-rigid mirror architecture approach demonstrated here is a precursor to the mirror technology being applied to the James Webb Space Telescope (JWST).
A series of developmental as well as flight mirrors have been in process over the last few years for IR cryogenic telescope applications such as the Space Infrared Telescope Facility (SIRTF) and the Next Generation Space Telescope (NGST) and for visible ambient systems such as Space Based Laser (SBL). We will discuss the performance of the 0.85-m SIRTF primary mirror (26.6 kg/m2 areal density) and the 0.5-m Subscale Beryllium Mirror Demonstrator (SBMD) beryllium mirror (9.8 kg/m2 areal density) as well as the current status of the 1.4-m Ball semi-rigid, beryllium Advanced Mirror System Demonstrator (AMSD). The AMSD mirror itself has an areal density of 10.4 kg/m2 and is currently in polishing. The entire AMSD assembly including composite reaction structure, flexures, and actuators, has an areal density less than 15 kb/m2.
Cyrogenic test results of the SIRTF and SBMD mirrors will be presented along with test data on the AMSD actuators. The SBMD mirror wsa cryofigured based on ambient and cryo testing to achieve a wavefront quality of 19 nm rms at 35 K. In addition, the effects of optically coating SBMD with a protected gold multi-layer system will be shown - demonstrating that a lightweight mirror can be coated without adverse print-through due to coating stress at ambient or cryo operating temperatures.
This paper provides a summary of the cryogenic performance of the SIRTF optical system. The SIRTF optical system includes a primary mirror, a secondary mirror, a metering structure, an interface simulator and an autocollimation test flat. For each of these elements, the room temperature and cryogenic performance has been established.
NASA's Space Infrared Telescope Facility (SIRTF) is a 1- meter class cryogenically-cooled space observatory. The constituent sub-assemblies are currently in their assembly and verification phase. To facilitate the assembly and verification of the telescope, the Space Telescope Test Facility (STTF) has been built at the Jet Propulsion Laboratory. The STTF allows for the assembly, alignment, and optical characterization of individual components, as well as the telescope assembly with its cryogenic mechanism, at temperatures from 300 to 5 K in a chamber with interior diameter of 1.4 m, and a height of 2.3 m. The chamber is surrounded by a class 10,000 or better clean room. This paper reports on the functional and operational capabilities of this facility.
This paper reports the results of the Space Infrared Telescope Facility (SIRTF) prototype telescope build conducted by Ball Aerospace and Technologies Corporation. The components for the SIRTF prototype telescope were designed and built under NASA's Infrared Telescope Technology Testbed program; the build and subsequent test activities were conducted under NASA's SIRTF/CTA flight program. The flight mission of the telescope will be astronomical observations in the infrared spectrum, 3.5 micrometers to 180 micrometers . To facilitate these observations the telescope will be cooled to 5.5 Kelvin and placed in a solar orbit aboard the SIRTF spacecraft. The prototype was built to verify the structural and cryogenic performance of the telescope.
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