The line emission mapper x-ray microcalorimeter instrument requires a 4 K cryogenic system to precool a continuous adiabatic demagnetization refrigerator enabling high-resolution x-ray spectroscopy. The cryogenic system described in this work provides the required structural and thermal environments using mature cooling and structural technologies. The system is comprised of a dewar design based on heritage manufacturing processes and an efficient four-stage pulse tube cryocooler with supporting control electronics.
The Ultraviolet/Optical/Infrared (UVOIR) flagship astrophysics architectures proposed by the Astro2020 Decadal Survey fundamentally challenge the current test-like-you-fly approach to space systems, because of their physical scale, multiple stages of on-orbit deployment, and extremely stringent optical performance requirements unique to visible-light coronagraphy. These limitations elevate the importance of integrated control, structural dynamics, and optical modeling, particularly in early system architecture studies. A unique non-contact observatory control architecture called Disturbance Free Payload (DFP) for next-generation large astrophysics observatories involves physically isolating the segmented telescope structure from the supporting spacecraft by means of a non-contact interface. In this control architecture, rigidbody telescope pointing is achieved by actuating the payload with non-contact voice coil actuators and maintaining positive interface gaps using spacecraft inertial actuators and interface non-contact sensors. This architecture presents distinct advantages over current state-of-the-art spacecraft vibration isolation approaches, particularly for large flexible spacecraft, but also introduces unique disturbance and coupling mechanisms that must be analyzed. In this paper, development of an integrated model is described, consisting of a 6.7-meter inscribed segmented optical system, and an unobscured telescope with 55 primary mirror segments. The paper starts with an overview of the models that directly predict time-domain lineof-sight and wavefront error dynamic stability (optics, dynamics, control system, error sources). Next, key dynamic stability performance metrics for coronagraph contrast performance are described and a systematic methodology for realizing an accurate but computationally feasible truncated modal model is presented. Finally, an exemplar point design that is compliant to 10-picometer RMS wavefront error is developed, and the necessary component errors to achieve this performance are presented.
The Origins Space Telescope will trace the history of our origins from the time dust and heavy elements permanently altered the cosmic landscape to present-day life. How did galaxies evolve from the earliest galactic systems to those found in the Universe today? How do habitable planets form? How common are life-bearing worlds? To answer these alluring questions, Origins will operate at mid- and far-infrared (IR) wavelengths and offer powerful spectroscopic instruments and sensitivity three orders of magnitude better than that of the Herschel Space Observatory, the largest telescope flown in space to date. We describe the baseline concept for Origins recommended to the 2020 US Decadal Survey in Astronomy and Astrophysics. The baseline design includes a 5.9-m diameter telescope cryocooled to 4.5 K and equipped with three scientific instruments. A mid-infrared instrument (Mid-Infrared Spectrometer and Camera Transit spectrometer) will measure the spectra of transiting exoplanets in the 2.8 to 20 μm wavelength range and offer unprecedented spectrophotometric precision, enabling definitive exoplanet biosignature detections. The far-IR imager polarimeter will be able to survey thousands of square degrees with broadband imaging at 50 and 250 μm. The Origins Survey Spectrometer will cover wavelengths from 25 to 588 μm, making wide-area and deep spectroscopic surveys with spectral resolving power R ∼ 300, and pointed observations at R ∼ 40,000 and 300,000 with selectable instrument modes. Origins was designed to minimize complexity. The architecture is similar to that of the Spitzer Space Telescope and requires very few deployments after launch, while the cryothermal system design leverages James Webb Space Telescope technology and experience. A combination of current-state-of-the-art cryocoolers and next-generation detector technology will enable Origins’ natural background-limited sensitivity.
For the Large Ultraviolet/Optical/Infrared Surveyor (LUVOIR) to perform high-contrast direct imaging of habitable exoplanets using a coronagraph instrument, the system must maintain extremely low system dynamic wavefront error (on the order of 10 picometers RMS over the spatial frequencies corresponding to the dark-hole region of the coronagraph) over a long time wavefront control sampling interval (typically 10 or more minutes). Meeting this level of performance requires a telescope vibration isolation system that delivers a high degree of dynamic isolation over a broad frequency range. A non-contact pointing and isolation system called the Vibration Isolation and Precision Pointing System (VIPPS) has been baselined for the LUVOIR architecture. Lockheed Martin has partnered with NASA to predict the dynamic wavefront error (WFE) performance of such a system, and mature the technology through integrated modeling, subsystem test and subscale hardware demonstration. Previous published results on LUVOIR dynamic WFE stability performance have relied on preliminary models that do not explicitly include the effects of a segmented Primary Mirror. This paper presents a study of predicted dynamic WFE performance of the LUVOIR-A architecture during steady-state operation of the coronagraph instrument, using an integrated model consisting of a segmented primary mirror, optical sensitivities, steering mirror and non-contact isolation, and control systems. The design assumptions and stability properties of the control system are summarized. Principal observatory disturbance sources included are control moment gyroscope and steering mirror exported loads. Finally, observatory architecture trades are discussed that explore tradeoffs between system performance, concept of operation and technology readiness.
The Origins Space Telescope will trace the history of our origins from the time dust and heavy elements permanently altered the cosmic landscape to present-day life. How did galaxies evolve from the earliest galactic systems to those found in the universe today? How do habitable planets form? How common are life-bearing worlds? To answer these alluring questions, Origins will operate at mid- and far-infrared wavelengths and offer powerful spectroscopic instruments and sensitivity three orders of magnitude better than that of Herschel, the largest telescope flown in space to date. After a 3 ½ year study, the Origins Science and Technology Definition Team will recommend to the Decadal Survey a concept for Origins with a 5.9-m diameter telescope cryocooled to 4.5 K and equipped with three scientific instruments. A mid-infrared instrument (MISC-T) will measure the spectra of transiting exoplanets in the 2.8 – 20 μm wavelength range and offer unprecedented sensitivity, enabling definitive biosignature detections. The Far-IR Imager Polarimeter (FIP) will be able to survey thousands of square degrees with broadband imaging at 50 and 250 μm. The Origins Survey Spectrometer (OSS) will cover wavelengths from 25 – 588 μm, make wide-area and deep spectroscopic surveys with spectral resolving power R ~ 300, and pointed observations at R ~ 40,000 and 300,000 with selectable instrument modes. Origins was designed to minimize complexity. The telescope has a Spitzer-like architecture and requires very few deployments after launch. The cryo-thermal system design leverages JWST technology and experience. A combination of current-state-of-the-art cryocoolers and next-generation detector technology will enable Origins’ natural backgroundlimited sensitivity.
The Origins Space Telescope (OST) will trace the history of our origins from the time dust and heavy elements permanently altered the cosmic landscape to present-day life. How did the universe evolve in response to its changing ingredients? How common are life-bearing planets? To accomplish its scientific objectives, OST will operate at mid- and far-infrared wavelengths and offer superlative sensitivity and new spectroscopic capabilities. The OST study team will present a scientifically compelling, executable mission concept to the 2020 Decadal Survey in Astrophysics. To understand the concept solution space, our team studied two alternative mission concepts. We report on the study approach and describe both of these concepts, give the rationale for major design decisions, and briefly describe the mission-enabling technology.
The design process for an opto-mechanical sub-system is discussed from requirements development through test. The process begins with a proper mission understanding and the development of requirements for the system. Preliminary design activities are then discussed with iterative analysis and design work being shared between the design, thermal, and structural engineering personnel. Readiness for preliminary review and the path to a final design review are considered. The value of prototyping and risk mitigation testing is examined with a focus on when it makes sense to execute a prototype test program. System level margin is discussed in general terms, and the practice of trading margin in one area of performance to meet another area is reviewed. Requirements verification and validation is briefly considered. Testing and its relationship to requirements verification concludes the design process.
The optics train of the Near Infrared Camera (NIRCam) instrument for NASA's James Webb Space Telescope (JWST)
includes a pick-off mirror (POM) mounted in the focus and alignment mechanism (FAM). Over the course of the
mission, the POM will have a narrow view of the L2 space environment. Charged particles will impinge and collect on
the mirror surface increasing the possibility of arcing to the adjacent baffle. A technique to ground the POM and remove
accumulated charge has been qualified and implemented on the flight instrument. This paper will provide an overview of
the qualification process including cryogenic resistance measurements, vibration testing and optical surface error
measurements. To measure the efficiency of this grounding technique, a POM engineering model was exposed to
representative mission electron fluence and results with the POM grounded and ungrounded will be presented.
The Near Infrared Camera (NIRCam) instrument for NASA's James Webb Space Telescope (JWST) has an optical prescription which terminates at two focal plane arrays for each module. The instrument will operate at 37K after experiencing launch loads at 293K. The focal plane array housings (FPAHs), including stray light baffles (SLBs) must accommodate all associated thermal and mechanical stresses. In addition, the stray light baffles must be installed in situ on the previously assembled flight modules. The main purpose of the FPAH SLBs is to effectively attenuate mission limiting stray light on the focal planes. This paper will provide an overview of the NIRCam stray light baffle design, mechanical and optical analysis, hardware implementation and test results.
The near infrared camera (NIRCam) instrument for NASA is one of four science instruments installed into
the integrated science instrument module (ISIM) of the James Webb space telescope (JWST) intended to
conduct scientific observations over a five year mission lifetime. The NIRCam instrument will have a pupil
imaging lens actuator assembly (PIL) to provide a means of imaging the primary mirror for ground testing,
instrument commissioning, and diagnostics which must operate from 293 - 37 Kelvin and be in support of
the usual launch environments.
More refined optic prescriptions and initial PIL vibration test data led to the redesign of the PIL. This paper
discusses the redesign of the lens mounts to accommodate a new optic prescription. This paper also details
the analysis of vibration test data that led to the redesign of a stiffer bearing mount for the PIL flight
mechanism that would ultimately be tested to show appropriate margins for meeting program vibration test
requirements.
The Near Infrared Camera (NIRCam) instrument for NASA's James Webb Space Telescope (JWST) has an optical
prescription which employs three triplet lens cells. The instrument will operate at 35K after experiencing launch loads at
~293K and the optic mounts must accommodate all associated thermal and mechanical stresses, plus maintain an
exceptional wavefront during operation. The Lockheed Martin Advanced Technology Center (LMATC) has built and
tested the collimator and camera optics for use on the NIRCam flight instrument. This paper presents an overview of the
driving requirements, a brief overview of the changes in the opto-mechanical design and analysis since our last
presentation, a discussion of the collimator and shortwave camera triplet assembly processes, and finally a summary of
the mechanical and optical test results.
The Near Infrared Camera (NIRCam) instrument for NASA's James Webb Space Telescope (JWST) has an optical
prescription which terminates at two focal plane arrays for each module. The instrument will operate at 35K after
experiencing launch loads at ~293K and the focal plane array housings must accommodate all associated thermal and
mechanical stresses, while keeping the FPAs aligned. The main purpose of the FPAH is to provide a stray light,
contamination, and radiation shield to the Focal Planes. The design includes a fold mirror used to direct incoming light
up to the detectors and mechanical support for the Application Specific Integrated Circuits (ASIC). A six degree of
freedom shim is used to align the Focal Plane Assembly at the operating temperature of 35 Kelvin. This paper will
provide an overview of the FPAH design including an update to the Fold Mirror design described in previous papers.
Analysis and test results of the ambient temperature optical and vibration testing will be presented.
The Near Infrared Camera (NIRCam) instrument for NASA's James Webb Space Telescope (JWST) has an optical
prescription which includes numerous fold mirror assemblies. The instrument will operate at 35K after experiencing
launch loads at ~293K. The optic mounts must accommodate all associated thermal and mechanical stresses, plus
maintain exceptional optical quality during operation. Lockheed Martin Space Systems Company (LMSSC) conceived,
designed, analyzed, assembled, tested, and integrated the mirror assemblies for the NIRCam instrument. This paper
covers the design, analysis, assembly, and test of two of the instruments key fold mirrors.
The Near Infrared Camera (NIRCam) instrument for NASA's James Webb Space Telescope (JWST) includes numerous
optical assemblies. The instrument will operate at 35K after experiencing launch loads at ~293K and the optic mounts
must accommodate all associated thermal and mechanical stresses, plus maintain exceptional optical quality during
operation. Lockheed Martin Space Systems Company (LMSSC) conceived, designed, analyzed, assembled, tested, and
integrated the optical assemblies for the NIRCam instrument. With using examples from NIRCam, this paper covers
techniques for mounting small mirrors and lenses for cryogenic space missions.
The Near Infrared Camera for the James Webb Space Telescope is designed to operate at a temperature of 37K. The
instrument must be assembled and aligned at room temperature. The optical design is refractive and incorporates several
different lens materials in addition to several mirrors which make an athermal design very difficult. All of the instrument
components are designed so that the instrument can come into alignment at 37K after assembly at room temperature. The
methods to predict alignment shifts are presented in this paper.
The Focus and Alignment Mechanism (FAM) is an opto-mechanical, cryogenic mechanism that positions the Pick-Off
Mirror (POM) for the Near Infrared Camera of the James Webb Space Telescope. The POM is used to direct the light
collected by the telescope into the Near Infrared Camera. The POM is a spherical, fused silica mirror. In order to retain
high surface quality at cryogenic temperatures, the POM is attached to the mechanism via a titanium flexure-mount
assembly. Three linear actuators are employed to position the POM in tip, tilt and piston. These linear actuators are
stepper motor driven, with harmonic drive gear reduction. In this paper, we will summarize the design and role of this
opto-mechanical mechanism and present the results of the environmental testing of the Engineering Test Unit. The tests
performed were thermal-vacuum cryogenic cycling, and vibration testing.
The mechanical design of any optic mount requires an understanding of the sensitivities of the optical design. The design of the filter optic mounts used on the James Webb Space Telescope - NIRCam filter
wheel assemblies have been designed to support the optics in a manner that does not compromise optical performance, while coping with several environmental conditions. We will review the design of the NIRCam filter optic assemblies and confirm the merits of the approach chosen to mount the optics, considering thermal, vibration and stress effects.
The Near Infrared Camera (NIRCam) is the primary imaging instrument on the James Webb Space Telescope. The
primary structure for NIRCam is called the Optical Bench Assembly (OBA). The OBA is a bonded Beryllium structure
designed to operate at 35K. The structure has recently undergone thermal cycling to 35K followed by structural
qualification vibration testing. Analytical predictions were made of the structural performance during vibration. These
predictions closely matched the actual performance. This paper summarizes the build and assembly of the OBA, and
focuses on the qualification thermal and structural testing of the OBA. The qualification testing is described and pre-test
analysis is presented and compared with test results.
The Near Infrared Camera (NIRCam) Optical Bench Assembly (OBA) is a I-220H beryllium adhesively-bonded
structure designed to operate at 35K. To support design activities, an adhesive testing program was performed, with
particular emphasis on adhesive allowables at 35K. The geometries of the samples were designed to emulate the
structural features of the OBA. The testing program is described, test data presented, and the results applied to the NIRCam OBA.
The Near Infrared Camera (NIRCam) for the James Webb Space Telescope (JWST) has undergone Pathfinder
component testing and evaluation. This paper presents the opto-mechanical test results. An overview of the optomechanical
system requirements is provided, followed by a discussion of the opto-mechanical system design and
assembly process. Tolerances in the opto-mechanical system as they relate to system level alignment are also presented.
Mechanical analysis related to vibration and thermal behavior of the design is shown. Finally, the overall performance
of the opto-mechanical system is discussed as it relates to instrument optical performance.
The Near Infrared Camera (NIRCam) instrument for NASA's James Webb Space Telescope (JWST) has an optical
prescription which employs several mirrors, some of which are powered and some of which are flats that aid in
packaging. Two distinct designs for the mirrors and their mounts have been developed such that different requirements
for mass, packaging and induced wavefront error can be met. The instrument will operate at 37K after experiencing
launch loads at ~293K and the mounts must accommodate all associated thermal and mechanical stresses. Two of the
mirrors needed to be redesigned after initial prototype testing of one of the designs. This paper will provide an update
on the design and analysis status for all the mirrors including results of the initial prototype testing.
Raytheon's Santa Barbara Remote Sensing (SBRS) division designed and built the MTSAT-1R Japanese Advanced Meteorological Imager for the Japanese Ministry of Transport between March, 1999 and July, 2002. In order to meet the stressing requirements of a geosynchronous orbit, a combination of structural, thermal, and optical (STOP) analyses were used to design and optimize the beryllium three-mirror anastigmat (TMA) telescope. This modeling approach was used to characterize and minimize the thermal distortion around local midnight. On-orbit temperatures and structural deformations were predicted using thermal Desktop/SINDA and PATRAN/NASTRAN software, respectively. The resulting optical performance was evaluated using Raytheon developed HEXAGON software. The telescope design was successfully optimized to attain specified visible channel performance for most of the 24 hour orbit.
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