This paper reports on the exposure of visible wavelength camera optical elements to a simulated orbital radiation environment in support of the Restore-L flight project at NASA’s Goddard Space Flight Center. Borosilicate glasses with various metal oxide dopants - S-LAL8, S-LAL18, N-SF1, and the polycarbonate material Makrolon GP were exposed to electrons and protons of varying energies. Low energy (E ≤ 10keV) charged particles were used primarily to assess degradation to the antireflective coatings of the optical elements. High energy (E ~ 1 MeV) charged particles were used to evaluate degradation to the bulk material. Elements of S-LAL18, N-SF1, LaK9G15, and Makrolon GP were exposed to a representative atomic oxygen rich environment. Elements of S-LAL8 and Makrolon GP were exposed to intense ultraviolet radiation. Pre- and post-exposure transmittance measurements were used to quantify the effects on the elements tested in the simulated environment over the 0.3 to 1.2 micron wavelength range. Our measurement results will be discussed in the context of their robustness to the orbital environment and the known chemical constituents of the materials tested.
Disordered thin film SiO2/SiOx coatings undergoing electron-beam bombardment exhibit cathodoluminescence, which can produce deleterious stray background light in cryogenic space-based astronomical observatories exposed to high energy electron fluxes from space plasmas. As future observatory missions push the envelope into more extreme environments and more complex and sensitive detection, a fundamental understanding of the dependencies of this
cathodoluminescence becomes critical to meet performance objectives of these advanced space-based observatories.
Measurements of absolute radiance and emission spectra as functions of incident electron energy, flux, and power
typical of space environments are presented for thin (~60-200 nm) SiO2/SiOx optical coatings on reflective metal substrates over a range of sample temperatures (~40-400 K) and emission wavelengths (~260-5000 nm). Luminescent
intensity and peak wavelengths of four distinct bands were observed in UV/VIS/NIR emission spectra, ranging from 300
nm to 1000 nm. A simple model is proposed that describes the dependence of cathodoluminescence on irradiation time,
incident flux and energy, sample thickness, and temperature.
This paper will review the suitability of the common four types of reflecting surfaces – Ag, Al, Au and Be - for use
aboard satellite borne remote sensing and astrophysical observatories, from the uv to far-ir spectral bands. The choice
of appropriate protecting and reflectance enhancing overcoats for these reflecting metals will be discussed. Laboratory
test data and optical diagnostic techniques used to verify durability of the selected coatings in a terrestrial storage
environment and their sensitivity to a space radiation and cold temperature environment will be presented. For some of
the selected coatings, a connection will be made between pre-launch laboratory quality checks and post-launch
performance on orbit.
Pre-launch acceptance testing and evaluation of mirrors coated for use in space are almost never performed on the
actual flight mirror. Smaller witness mirrors, coated at the same time as the flight component, are used as test proxies
for the spaceflight component. The intent of the acceptance testing is generally aimed at identifying any mirror surface
quality problems before the larger mirror experiences qualification testing that usually occurs at the assembled
instrument level when recovery from a previously undetected flaw can be costly. Only in rare cases will the testing of a
smaller proxy sample reveal a mirror’s substrate structural flaws. This presentation will discuss details associated with
pre-launch radiation sensitivity and cryogenic acceptance testing of the commonly used mirror reflector coatings aboard
space optical instruments. The sufficiency of reflectance and transmittance measurements as the primary diagnostic tool
for evaluating mirror coating quality, and as a predictor of on-orbit performance, will be emphasized with reference to
specific space missions.
James Webb Space Telescope (JWST) Optical Telescope Element (OTE) mirror coating program has been completed.
The science goals of the JWST mission require a uniform, low stress, durable optical coating with high reflectivity over
the JWST spectral region. The coating has to be environmentally stable, radiation resistant and compatible with the
cryogenic operating environment. The large size, 1.52 m point to point, light weight, beryllium primary mirror (PM)
segments and flawless coating process during the flight mirror coating program that consisted coating of 21 flight
mirrors were among many technical challenges. This paper provides an overview of the JWST telescope mirror coating
program. The paper summarizes the coating development program and performance of the flight mirrors.
The James Webb Space Telescope (JWST) is a general astrophysics mission which consists of a 6.6m diameter,
segmented, deployable telescope for cryogenic IR space astronomy (~35K). The JWST Observatory architecture
includes the Optical Telescope Element and the Integrated Science Instrument Module (ISIM) element that contains four
science instruments (SI) including a Guider.
The alignment philosophy of ISIM is such that the cryogenic changes in the alignment of the SI interfaces are captured in
the ISIM alignment error budget. The SIs are aligned to the structure's coordinate system under ambient, clean room
conditions using laser tracker and theodolite metrology. The ISIM structure is thermally cycled and temperature-induced
structural changes are concurrently measured with a photogrammetry metrology system to ensure they are within
requirements.
We compare the ISIM photogrammetry system performance to the ISIM metrology requirements and describe the
cryogenic data acquired to verify photogrammetry system level requirements, including measurement uncertainty. The
ISIM photogrammetry system is the baseline concept for future tests involving the Optical Telescope Element (OTE) and
Observatory level testing at Johnson Space Flight Center.
A warm window surface with a relatively high (>50%) surface emittance can add significant undesired heat loading into a cryogenic test chamber. However, a front surface coating that consists of a very thin adherent layer of evaporated Cr that is overcoated with about 7nm of evaporated Au has been demonstrated to
reduce the inherently high emittance of a glass or sapphire window surface down to about 14%, while maintaining a visible transmittance in excess of 55%. The coating possesses reasonably good adhesion and cleaning durability when deposited onto glass or sapphire substrates and has survived multiple temperature cycles between 316K and 20K. The addition of a single layer anti-reflection coating, such as reactively evaporated SiOx, to the otherwise uncoated exterior surface of a cryogenic window produced a further increase in visible wavelength transmittance without altering window emittance. This paper will present measured reflectance, transmittance, and emittance data for the Cr + Au window surface coating relevant to
a cryogenic window application.
This paper presents the results of the hypervelocity projectile bombardment of a gold-coated beryllium substrate telescope mirror. Individual latex (ρ = 1.1 g/cm3) and iron (7.9 g/cm3) projectiles, in the size range 0.70 to 1.44μm (avg. mass = 0.24 - 7.1 x 10-15 kg), representative of interplanetary dust, with velocities from 2 - 20 km/s, created impact craters in the composite mirror structure that were approximate hemispheres. The ratio of impact damage diameter to projectile energy was found experimentally to be close to 0.1μm/nJ for both latex and iron projectiles. These dimension data, combined with recent measurements of interplanetary and interstellar dust fluxes, can be used to estimate expected space telescope mirror surface damage and scattering increase due to hypervelocity dust impacts.
Flat surfaces of reaction bonded SiC and aspheric surfaces of Si clad reaction bonded SiC were polished to yield rms surface roughnesses less than 30Å. These surfaces were then overcoated with two formulations of a typical front surface protected silver film and their reflectances and roughnesses compared with highly polished fused silica flat surfaces that were silver coated at the same time. Surface roughness and BRDF measurements performed before and after coating with protected silver indicated no significant increase in surface roughness or measured scatter for either silver coating formulation and a barely detectable measured roughness difference between the two coating formulations.
The twin composite structure telescopes aboard the Microwave Anisotropy Probe were selectivity roughened to reduce focused solar radiance. They were then overcoated with evaporated A1 + reactively evaporated silicon oxide films whose respective thicknesses were sufficient to achieve the high reflectance of bulk aluminum at the microwave operating frequencies; high emittance in the thermal emittance region; and moderately low solar absorptance for a resultant (alpha) /(epsilon) < 0.9. This report will discuss the experimental techniques used to prepare the telescope reflector surfaces and to evaluate their resultant properties.
Mirror coatings designed for use on satellite remote sensing instruments were exposed to a simulated geostationary orbit radiation flux of combined ultraviolet, electron, and proton radiation. Reflectance measured in vacuum before, during, and after exposure demonstrated that some mirror coatings are much more resistant to damage than others. The laboratory test results agree with in-orbit mirror temperature increases observed on GOES satellite instruments. The laboratory tests also confirm the necessity of measuring reflectance change in vacuum, due to the rapid recovery of reflectance loss upon exposure to room atmosphere.
This paper will present measured reflectance, transmittance, surface figure and roughness data for KBr and ZnSe beamsplitters and compensators that were made for use on spaceflight Michelson-type Fourier transform spectrometers. Measured data for visible and infrared wavelengths, at room temperature and cryogenic temperatures, will be shown. Calculated performance data for KCl substrates will be included for comparison.
The Composite Infrared Spectrometer (CIRS) instrument on the Cassini Mission launched in October of 1997. The CIRS instrument contains a mid-infrared (MIR) and a far-infrared interferometer and operates at 170 Kelvin. The MIR is a Michelson Fourier transform spectrometer utilizing a 76 mm (3 inch) diameter potassium bromide beamsplitter and compensator pair. The potassium bromide elements were tested to verify effects of cooldown and vibration prior to integration into the instrument. The instrument was then aligned to ambient temperatures, tested cryogenically and re-verified after vibration. The stringent design optical figure requirements for the beamsplitter and compensator included fabrication errors, mounting stress and vibration load effects. This paper describes the challenges encountered in mounting the elements to minimize distortion and to survive vibration.
An estimate of the transparency of aluminized mylar `superinsulation' was obtained by measuring the far- infrared/submillimeter wave transmittances of 3 pieces randomly selected from a 25.4 micrometers -thick (nom. 001 in.) sheet of mylar that was aluminized on one side. Measured transmittance values were less than 1 X 10-4 in the 100 micrometers - 1000 micrometers wavelength region. The emissivities of mylar and aluminum were computed from published optical constants to be, respectively, about 5 X 10-2 and 2 X 10-4 for temperatures near 20 K and an effective wavelength of 150 micrometers . Due to the strong attenuation of the aluminum layer, the radiant power from an elemental area on the outer surface of the superinsulation is about 104 times more significant than radiance originating within the insulating mylar layer, for temperatures near 20 K. Radiant power passing through doubly aluminized mylar (the usual configuration) would be attenuated by a factor of about 10-10.
Measured infrared reflectance and transmittance data, as a function of wavelength and incidence angle, are presented for polarization inducing components on a typical Geostationary Operational Environmental Satellite (GOES) atmospheric sounding instrument. The data are then used to construct Mueller matrices from which instrument polarization sensitivity, not only to incoming radiance from an observed scene, but also to the instrument's own radiant signature. A comparison is made between the polarizing characteristics of a typical filter-type infrared sounding radiometer and a proposed Micheson-type FOurier transform alternative.
A topical workshop on Cryogenic Optical Systems and Instruments was held on Monday 4 April, from 8:00 to 10:00 pm, moderated by James B. Heaney, NASA Goddard Space Flight Center.
The simultaneous measurement of the spectrally and spatially variant transmittance of a linear variable order-sorting filter in a manner that closely resembles its conditions of actual use is described. The transmittance of a prototype order-sorting filter was measured in the 400- to 880-nm wavelength region by illuminating it with the output beam of a spectrophotometer while the filter was attached to the front of a 30 x 32 pixel silicon array detector. The filter was designed to be used in the output beam of a grating spectrometer to prevent the dispersal of higher diffracted orders onto an array detector. Areas of the filter that were spatially matched to the corresponding detector pixel column had measured peak transmittances of about 90% that were uniform to within ±1.5% along a given column. Transmittances for incident wavelengths shorter than the desired bandpass, corresponding to the order overlap region, were measured in the 3 x 10-3 range. Line spread function measurements made with the array detector indicated no significant beam spreading caused by inserting the filter into the beam.
This paper will present transmittance data, in the 1- to 1000-micron wavelength region, at temperatures from 300K down to near 4K, for a selection of filters composed of multilayer thin films on transmitting substrates, reststrahlen crystals, mesh-grid elements, and hybrids of these types. Polyethylene laminates and vapor deposited parylene will be compared as antireflection layers for high refractive index infrared crystals at long wavelengths.
This report will describe the status of an effort to catalog the refractive index, absorption, reflectance and transmittance of selected IR transmitting materials over the wavelength range from 1 to 1000 microns, and at temperatures from 300 to about 2 K. Data are presented for LiF, CaF2, BaF2, KBr, and TlBr, as well as for KRS-5 (TlBr-I) and KRS-6 (TlBr-Cl). A cryooptical measurements facility at NASA-Goddard, which has been used to generate some of the cataloged data, is also described.
This paper will discuss the scientific and technological motivations for cleaning and re-coating optical surfaces, including solar power and thermal control surfaces, in the vacuum of space. Hardware concepts and their associated problems will also be addressed.
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