iLocater is a new, near-infrared, extreme precision radial velocity (EPRV) spectrograph under construction for the dual 8.4m diameter Large Binocular Telescope (LBT). The instrument uses single-mode fibers (SMFs) injected with adaptive optics for illumination. We present the integration process for the spectrograph and cryostat systems, and the laboratory performance testing that has been completed. Testing has included optical performance characterization at ambient and cryogenic temperatures, assessment of cryogenic thermal control of the system (80-100K) at sub-mK level, and instrument detector performance (an H4RG-10). The optimized spectrograph and cryostat system will be delivered to the LBT in 2024.
NASA’s Dragonfly mission will sample surface materials from multiple sites on Saturn’s largest moon, Titan, in exploration of prebiotic chemistry. We report on the performance of our short-pulsed UV laser transmitter, developed for the Dragonfly’s on-board Mass Spectrometer (DraMS). Our Engineering Test Unit (ETU) has completed flight qualification and demonstrated its operational science requirements, such that the final spaceflight unit build can begin. The Titan Hydrocarbon Analysis Nanosecond Optical Source (THANOS) ETU laser produces 266 nm laser pulses at programmable energy levels to perform high resolution Laser Desorption Mass Spectrometry (LDMS) measurements. The laser operates in bursts of one to 50 pulses, each at ⪅ 2 ns pulse width with a pulse energy of 0 - 200 uJ, at a 100 Hz repetition rate. This paper details the qualification process of the THANOS laser as well as the rigorous characterization performed to ensure consistent performance of the system during laboratory testing, while integrated onto the DraMS instrument and most critically, while operating on the distant surface of Titan.
NASA’s Dragonfly mission is a rotorcraft lander which will explore several geologic locations on Saturn’s moon, Titan and investigate evidence of surface-level prebiotic chemistry as well as search for chemical signatures of water-based and/or hydrocarbon-based life. To perform molecular composition investigations in-situ, the payload includes the Dragonfly Mass Spectrometer (DraMS), being developed at NASA’s Goddard Space Flight Center (GSFC). DraMS will utilize laser desorption mass spectrometry (LDMS) to interrogate surface samples and measure the organic composition. Enabling this science capability is the Throttled Hydrocarbon Analysis by Nanosecond Optical Source (THANOS) laser being developed at NASA-GSFC. The THANOS laser is comprised of a solid state, passively Q-Switched Nd:YAG oscillator which is frequency converted to 266 nm and utilizes a RTP high voltage electro-optic for pulse energy control. The laser outputs <2.0 ns pulses with a maximum energy of approximately 200 uJ which can be emitted in 1 - 50 shot bursts at 100 Hz while performing LDMS science operations. The laser has the capability to throttle its UV pulse energy output from full attenuation to maximum energy to provide varying levels of fluence on samples in the DraMS instrument. We report on the THANOS’ laser technology development and space qualification effort including vibration, thermal vacuum cycling, radiation as well as optical damage testing due to Titan’s atmospheric composition, performed at NASA-GSFC from 2019 through 2022.
The Ocean Color Instrument (OCI), which will be integrated with the Plankton, Aerosol, Cloud, ocean Ecosystem (PACE) satellite, will collect science data that will be used to monitor the health of Earth’s oceans and atmosphere. The Short-Wave Infrared (SWIR) Detection Assembly (SDA), built and characterized by Utah State University Space Dynamics Laboratory (SDL), is a subsystem of OCI consisting of 32 channels covering seven discrete optical bands of interest. A total of 16 SWIR Detection Subassemblies (SDSs) compose the SDA and house the cold optical system. The science data optical input for each SDS is supplied by a 0.22 NA multimode fiber interfacing with a fiber adapter. The diverging light from the fiber is collimated, split by a dichroic beamsplitter to two separate channels, filtered by the science filter, and then reimaged onto the single-element detectors with a final 0.76 NA. Aspheric, diamond-turned powered elements are used throughout the optical design. Fabrication and alignment tolerance analysis/budgets are balanced to ensure the optical system meets throughput requirements. All systems are aligned at ambient temperature using an InSb camera and an in-line illumination microscope system to directly image the active detector area through the science filters. Compensators used during alignment are detector focus and decenter, which are adjusted via photoetched shims in increments of 25 μm. Average focus and centering errors were less than 8 μm among all 32 flight and 10 flight spare detectors. Each SDS spectral response and conversion gain was verified at operational temperature of -65°C in vacuum.
For the past 25 years, the National Aeronautics and Space Administration (NASA) Goddard Space Flight Center’s Photonics Group in the Engineering Directorate has been substantially contributing to the flight design, development, production, testing and integration of many science and navigational instruments. The Moon to Mars initiative will rely heavily upon utilizing commercial technologies for instrumentation with aggressive schedule deadlines. The group has an extensive background in screening, qualifying, development and integration of commercial components for spaceflight applications. By remaining adaptable and employing a rigorous approach to component and instrument development, they have forged and fostered relationships with industry partners. They have been willing to communicate lessons learned in packaging, part construction, materials selection, testing, and other facets of the design and production process critical to implementation for high-reliability systems. As a result, this successful collaboration with industry vendors and component suppliers has enabled a history of mission success from the Moon to Mars (and beyond) while balancing cost, schedule, and risk postures. In cases where no commercial components exist, the group works closely with other teams at Goddard Space Flight Center and other NASA field centers to fabricate and produce flight hardware for science, remote sensing, and navigation applications. Summarized here is the last ten years of instrumentation development lessons learned and data collected from the subsystems down to the optoelectronic component level.
The Global Ecosystem Dynamics Investigation (GEDI) instrument was designed, built, and tested in-house at NASA’s Goddard Space Flight Center and launched to the International Space Station (ISS) on December 5, 2018. GEDI is a multibeam waveform LiDAR (light detection and ranging) designed to measure the Earth’s global tree height and canopy density using 8 laser beam ground tracks separated by roughly 600 meters. Given the ground coverage required and the 2 year mission duration, a unique optical design solution was developed. GEDI generates 8 ground sampling tracks from 3 transmitter systems viewed by a single receiver telescope, all while maximizing system optical efficiency and transmitter to receiver boresight alignment margin. The GEDI optical design, key optical components, and system level integration and testing are presented here. GEDI began 2 years of science operations in March 2019 and so far, it is meeting all of its key optical performance requirements and is returning outstanding science.
The United States, National Aeronautics and Space Administration (NASA) Goddard Space Flight Center (GSFC), Fiber Optics Team in the Electrical Engineering Division of the Applied Engineering and Technology Directorate, designed, developed and integrated the space flight optical fiber array hardware assemblies for the Lunar Reconnaissance Orbiter (LRO). The two new assemblies that were designed and manufacturing at NASA GSFC for the LRO exist in configurations that are unique in the world for the application of ranging and lidar. These assemblies were developed in coordination with Diamond Switzerland, and the NASA GSFC Mechanical Systems Division.
The assemblies represent a strategic enhancement for NASA’s Laser Ranging and Laser Radar (LIDAR) instrument hardware by allowing light to be moved to alternative locations that were not feasible in past space flight implementations. An account will be described of the journey and the lessons learned from design to integration for the Lunar Orbiter Laser Altimeter and the Laser Ranging Application on the LRO. The LRO is scheduled to launch end of 2008.
ChemCam is an instrument suite on the Mars Science Laboratory (MSL) mission that will launch to Mars in 2011. MSL is a rover-type lander that is capable of exploring large territories over the mission lifetime and includes a number of instruments for analysing rocks and soil. ChemCam includes a laser induced breakdown spectroscopy (LIBS) [1] instrument that samples the surface chemistry of target objects within about 10 m of the rover without having to physically move to the target to obtain emission spectra in the 240 nm to 800 nm range. The ChemCam laser and sensing telescope are mounted on the rover Remote Sensing Mast (RSM) and have 360 degrees of azimuthal range, and 180 degrees of vertical range, allowing sampling of any object within range and line-of-sight of the mast top. This capability can be used to select targets for further analysis by other MSL instruments.
The LIBS portion of ChemCam is split between the top of the RSM and inside the rover body. The laser and the telescope are located atop the mast and rotate to select and observe targets. The three spectrometers (UV, VIS, and NIR) are located inside the rover body, along with a demultiplexer (demux) that splits the signal into the three bands. The signal from the telescope is transmitted to the demux by the fiber optic cable that is the subject of this paper. The fiber optic cable (FOC) is a single 5.7-m long, broadband, mult-mode fiber that connects the telescope and demux and is exposed to the full martian environment in some places and subjected to significant temperature gradients as it runs from interior areas to exterior areas.
Laser spectral analysis systems are increasingly being considered for in situ analysis of the atomic and molecular composition of selected rock and soil samples on other planets [1][2][3]. Both Laser Induced Breakdown Spectroscopy (LIBS) and Raman spectroscopy are used to identify the constituents of soil and rock samples in situ. LIBS instruments use a high peak-power laser to ablate a minute area of the surface of a sample. The resulting plasma is observed with an optical head, which collects the emitted light for analysis by one or more spectrometers. By identifying the ion emission lines observed in the plasma, the constituent elements and their abundance can be deduced. In Raman spectroscopy, laser photons incident on the sample surface are scattered and experience a Raman shift, exchanging small amounts of energy with the molecules scattering the light. By observing the spectrum of the scattered light, it is possible to determine the molecular composition of the sample.
For both types of instruments, there are advantages to physically separating the light collecting optics from the spectroscopy optics. The light collection system will often have articulating or rotating elements to facilitate the interrogation of multiple samples with minimum expenditure of energy and motion. As such, the optical head is often placed on a boom or an appendage allowing it to be pointed in different directions or easily positioned in different locations. By contrast, the spectrometry portion of the instrument is often well-served by placing it in a more static location. The detectors often operate more consistently in a thermally-controlled environment. Placing them deep within the spacecraft structure also provides some shielding from ionizing radiation, extending the instrument’s useful life. Finally, the spectrometry portion of the instrument often contains significant mass, such that keeping it off of the moving portion of the platform, allowing that portion to be significantly smaller, less massive and less robust.
Large core multi-mode optical fibers are often used to accommodate the optical connection of the two separated portions of such instrumentation. In some cases, significant throughput efficiency improvement can be realized by judiciously orienting the strands of multi-fiber cable, close-bunching them to accommodate a tight focus of the optical system on the optical side of the connection, and splaying them out linearly along a spectrometer slit on the other end.
For such instrumentation to work effectively in identifying elements and molecules, and especially to produce accurate quantitative results, the spectral throughput of the optical fiber connection must be consistent over varying temperatures, over the range of motion of the optical head (and it’s implied optical cable stresses), and over angle-aperture invariant of the total system. While the first two of these conditions have been demonstrated[4], spectral observations of the latter present a cause for concern, and may have an impact on future design of fiber-connected LIBS and Raman spectroscopy instruments. In short, we have observed that the shape of the spectral efficiency curve of a large multi-mode core optical fiber changes as a function of input angle.
Lasers with high peak power pulses are commonly used in spaceflight missions for a wide range of applications, from LIDAR systems to optical communications. Due to the high optical power needed, the laser has to be located on the exterior of the satellite or coupled through a series of free space optics. This presents challenges for thermal management, radiation resistance, and mechanical design. Future applications will require multiple lasers located close together, which further complicates the design. Coupling the laser energy into a fiber optic cable allows the laser to be relocated to a more favorable position on the spacecraft. Typical fiber optic termination procedures are not sufficient for injection of these high-power laser pulses without catastrophic damage to the fiber endface. In the current study, we will review the causes of fiber damage during high-power injection and discuss our new manufacturing procedures that overcome these issues to permit fiber use with high reliability in these applications. We will also discuss the proper methods for launching the laser pulses into the fiber to avoid damage and how this is being implemented for current spaceflight missions.
Fiber optic assemblies have been used on spaceflight missions for many years as an enabling technology for routing, transmitting, and detecting optical signals. Due to the overwhelming success of NASA in implementing fiber optic assemblies on spaceflight science-based instruments, system scientists increasingly request fibers that perform in extreme environments while still maintaining very high optical transmission, stability, and reliability. Many new applications require fiber optic assemblies that will operate down to cryogenic temperatures as low as 20 Kelvin. In order for the fiber assemblies to operate with little loss in optical throughput at these extreme temperatures requires a system level approach all the way from how the fiber assembly is manufactured to how it is held, routed, and integrated. The NASA Goddard Code 562 Photonics Group has been designing, manufacturing, testing, and integrating fiber optics for spaceflight and other high reliability applications for nearly 20 years. Design techniques and lessons learned over the years are consistently applied to developing new fiber optic assemblies that meet these demanding environments. System level trades, fiber assembly design methods, manufacturing, testing, and integration will be discussed. Specific recent examples of ground support equipment for the James Webb Space Telescope (JWST); the Ice, Cloud and Land Elevation Satellite–2 (ICESat- 2); and others will be included.
The Advanced Topographic Laser Altimeter System (ATLAS) Instrument has been in integration and testing over the past 18 months in preparation for the Ice, Cloud and Land Elevation Satellite – 2 (ICESat-2) Mission, scheduled to launch in 2017. ICESat-2 is the follow on to ICESat which launched in 2003 and operated until 2009. ATLAS will measure the elevation of ice sheets, glaciers and sea ice or the “cryosphere” (as well as terrain) to provide data for assessing the earth’s global climate changes. Where ICESat’s instrument, the Geo-Science Laser Altimeter (GLAS) used a single beam measured with a 70 m spot on the ground and a distance between spots of 170 m, ATLAS will measure a spot size of 10 m with a spacing of 70 cm using six beams to measure terrain height changes as small as 4 mm.[1] The ATLAS pulsed transmission system consists of two lasers operating at 532 nm with transmitter optics for beam steering, a diffractive optical element that splits the signal into 6 separate beams, receivers for start pulse detection and a wavelength tracking system. The optical receiver telescope system consists of optics that focus all six beams into optical fibers that feed a filter system that transmits the signal via fiber assemblies to the detectors. Also included on the instrument is a system that calibrates the alignment of the transmitted pulses to the receiver optics for precise signal capture. The larger electro optical subsystems for transmission, calibration, and signal receive, stay aligned and transmitting sufficiently due to the optical fiber system that links them together. The robust design of the fiber optic system, consisting of a variety of multi fiber arrays and simplex assemblies with multiple fiber core sizes and types, will enable the system to maintain consistent critical alignments for the entire life of the mission. Some of the development approaches used to meet the challenging optical system requirements for ATLAS are discussed here.
We are developing a stable and precise spectrograph for the Large Binocular Telescope (LBT) named “iLocater.” The instrument comprises three principal components: a cross-dispersed echelle spectrograph that operates in the YJ-bands (0.97-1.30 μm), a fiber-injection acquisition camera system, and a wavelength calibration unit. iLocater will deliver high spectral resolution (R~150,000-240,000) measurements that permit novel studies of stellar and substellar objects in the solar neighborhood including extrasolar planets. Unlike previous planet-finding instruments, which are seeing-limited, iLocater operates at the diffraction limit and uses single mode fibers to eliminate the effects of modal noise entirely. By receiving starlight from two 8.4m diameter telescopes that each use “extreme” adaptive optics (AO), iLocater shows promise to overcome the limitations that prevent existing instruments from generating sub-meter-per-second radial velocity (RV) precision. Although optimized for the characterization of low-mass planets using the Doppler technique, iLocater will also advance areas of research that involve crowded fields, line-blanketing, and weak absorption lines.
The James Webb Space Telescope (JWST) requires testing of the full optical system in a cryogenic vacuum environment
prior to launch. Challenges with the telescope architecture and the test environment led to placing removable optical test
sources at the intermediate focus of this off-axis Three Mirror Anastigmat (TMA) to provide test sources in the Science
Instruments. Fiber optic cables will route light whose wavelength is between 600 and 2120 nm from photonics external
to the cryo-vacuum chamber to intermediate focus locations. These fiber optic cables will be greater than 50 meters in
length and transition from ambient (293K) temperatures outside the chamber to cryogenic (30K) temperatures at the
intermediate focus. Presented here are results from risk reduction testing conducted to ensure the fiber optic cables
selected will 1) transmit 2.12μm light over long fiber runs, 2) show strong macro bending performance, and 3) perform
at cryogenic temperatures.
The Jupiter Europa Orbiter (JEO) is NASA's element of the joint Europa Jupiter System Mission (EJSM). Based on
current trajectories, the spacecraft will spend a significant amount of time in the Jovian radiation belts. Therefore,
research endeavors are underway to study the radiation effects on the various parts and components needed to
implement the instruments. Data from these studies will be used for component selection and system design to ensure
reliable operation throughout the mission duration. The radiation environment en route to Jupiter is nothing new for
NASA designed systems, however, the long durations orbiting Jupiter and Europa present new challenges for radiation
exposure. High-energy trapped electrons and protons at Jupiter dominate the expected radiation environment.
Therefore, most of the initial component level radiation testing is being conducted with proton exposure. In this paper
we will present in-situ monitoring of the optical transmission of various laser optical components during proton
irradiation. Radiation induced optical attenuation of some components is less than would be expected, based on the
authors experiences, and is attributed to the interaction of the protons with the materials. The results are an encouraging
first step in screening these optical materials for spaceflight in a high radiation environment.
High power pulsed lasers are commonly deployed in harsh environments, like space flight and military missions, for a
variety of systems such as LIDAR, optical communications over long distances, or optical firing of explosives. Fiber
coupling of the laser pulse from the laser to where it is needed can often save size, reduce weight, and lead to a more
robust and reliable system. Typical fiber optic termination procedures are not sufficient for injection of these high
power laser pulses without catastrophic damage to the fiber endface. In the current study, we will review the causes of
fiber damage during high power injection and discuss methods used to avoid these issues to permit fiber use with high
reliability in these applications. A brief review of the design considerations for high peak power laser pulse injection
will be presented to familiarize the audience with all the areas that need to be considered during the design phase. The
majority of this paper focuses on the proper fiber polishing methods for high power use with an emphasis on laser
polishing of the fibers. Results from recently build fibers will be shown to demonstrate the techniques.
For the past decade NASA programs have utilized the Diamond AVIM connector for optical fiber assemblies on space
flight instrumentation. These connectors have been used in communications, sensing and LIDAR systems where
repeatability and high performance are required. Recently Diamond has released a smaller form factor optical fiber
connector called the "Mini-AVIM" which although more compact still includes the tight tolerances and the ratcheting
feature of the heritage AVIM. NASA Goddard Space Flight Center Photonics Group in the Parts, Packaging and
Assembly Technologies Office has been performing evaluations of this connector to determine how it compares to the
performance of the AVIM connector and to assess its feasibility for harsh environmental applications. Vibration and
thermal testing were performed on the Mini-AVIM with both multi-mode and single-mode optical fiber using insitu
optical transmission monitoring. Random vibration testing was performed using typical launch condition profiles for
most NASA missions but extended to 35 Grms, which is much higher than most requirements. Thermal testing was
performed incrementally up to a range of -55°C to +125°C. The test results include both unjacketed fiber and cabled
assembly evaluations. The data presented here indicate that the Mini-AVIM provides a viable option for small form
factor applications that require a high performance optical fiber connector.
Over the past ten years, NASA has studied the effects of harsh environments on optical fiber assemblies for
communication systems, lidar systems, and science missions. The culmination of this has resulted in recent technologies
that are unique and tailored to meeting difficult requirements under challenging performance constraints. This
presentation will focus on the past mission applications of optical fiber assemblies, including: qualification information,
lessons learned, and new technological advances that will enable the road ahead.
Fiber optic cables are widely used in modern systems that must provide stable operation during exposure to changing environmental conditions. For example, a fiber optic cable on a satellite may have to reliably function over a temperature range of -50°C up to 125°C. While the system requirements for a particular application will dictate the exact method by which the fibers should be prepared, this work will examine multiple ruggedized fibers prepared in different fashions and subjected to thermal qualification testing. The data show that if properly conditioned the fiber cables can provide stable operation, but if done incorrectly, they will have large fluctuations in transmission.
Fiber optic cables are increasingly being used in harsh environments where they are subjected to vibration. Understanding the degradation in performance under these conditions is essential for integration of the fibers into the given application. System constraints often require fiber optic connectors so that subsystems can be removed or assembled as needed. In the present work, various types of fiber optic connectors were monitored in-situ during vibration testing to examine the transient change in optical transmission and the steady-state variation following the event. The fiber endfaces and connectors were inspected at selected intervals throughout the testing.
The NASA Goddard Fiber Optics Team in the Electrical Engineering Division of the Applied Engineering and
Technology Directorate designed, developed and integrated the space flight optical fiber array hardware for the Lunar
Reconnaissance Orbiter (LRO). The two new assemblies that were designed and manufactured at GSFC for the LRO
exist in configurations that are unique in the world for the application of ranging and LIDAR. Described here is an
account of the journey and the lessons learned from design to integration for the Lunar Orbiter Laser Altimeter and the
Laser Ranging Application on the LRO.
Rare-earth-doped fibers, such as Er3+- and Yb3+-doped aluminosilicates can be advantageous in space-based systems
due to their stability, their high-bandwidth transmission properties and their lightweight, small-volume properties. In
such environments the effect of ionizing-radiation on the optical transmission of these fibers is of paramount importance.
For the present work, gamma-radiation experiments were conducted in which un-pumped Yb3+ and Er3+ doped sample
fibers were irradiated with a Cobalt-60 source under different dose-rate and temperature conditions. In-situ spectral
transmittance data over the near IR was monitored during the irradiations for total doses of up to tens of krad (Si). It was
found that there was a dose-rate dependence in which higher rates resulted in more photodarkening. Higher temperatures
were not found to significantly affect the rate of photodarkening at the dose rates used.
Sandia National Laboratories' program in high-power fiber lasers has emphasized development of enabling technologies
for power scaling and gaining a quantitative understanding of fundamental limits, particularly for high-peak-power,
pulsed fiber sources. This paper provides an overview of the program, which includes: (1) power scaling of diffraction-limited
fiber amplifiers by bend-loss-induced mode filtering to produce >1 MW peak power and >1 mJ pulse energy
with a practical system architecture; (2) demonstration of a widely tunable repetition rate (7.1-27 kHz) while
maintaining constant pulse duration and pulse energy, linear output polarization, diffraction-limited beam quality, and
<1% pulse-energy fluctuations; (3) development of microlaser seed sources optimized for efficient energy extraction; (4)
high-fidelity, three-dimensional, time-dependent modeling of fiber amplifiers, including nonlinear processes; (5)
quantitative assessment of the limiting effects of four-wave mixing and self-focusing on fiber-amplifier performance; (6)
nonlinear frequency conversion to efficiently generate mid-infrared through deep-ultraviolet radiation; (7) direct diode-bar
pumping of a fiber laser using embedded-mirror side pumping, which provides 2.0x higher efficiency and much
more compact packaging than traditional approaches employing formatted, fiber-coupled diode bars; and (8)
fundamental studies of materials properties, including optical damage, photodarkening, and gamma-radiation-induced
darkening.
Gamma-radiation-induced photodarkening has been observed and characterized in a suite of Yb-doped, Er-doped
and Yb/Er co-doped optical fibers. Significant reduction in the optical transmission of the fibers under passive (not
pumped) conditions was observed for wavelengths across the infrared spectrum. In general, it was found that the co-doped
fiber tested showed the strongest radiation resistance whereas the Er-doped fibers tested exhibited the greatest
radiation sensitivity. A dependence on dose rate was also observed in all fibers.
The deployment of optical fibers in adverse radiation environments, such as those encountered in a low-Earth-orbit
space setting, makes critical the development of an understanding of the effect of large accumulated ionizing-radiation
doses on optical components and systems. In particular, gamma radiation is known to considerably affect the
performance of optical components by inducing absorbing centers in the materials. Such radiation is present both as
primary background radiation and as secondary radiation induced by proton collisions with space-craft material.
This paper examines the effects of gamma radiation on erbium-, ytterbium-, and Yb/Er co-doped optical fibers by
exposing a suite of such fibers to radiation from a Co-60 source over long periods of time while monitoring the temporal
and spectral decrease in transmittance of a reference signal. For same total doses, results show increased photodarkening
in erbium-doped fibers relative to ytterbium-doped fibers, as well as significant radiation resistance of the co-doped
fibers over wavelengths of 1.0 - 1.6 microns. All three types of fibers were seen to exhibit dose-rate dependences.
A novel multi-mode 5-fiber array assembly was developed, manufactured, characterized and then qualified for the Lunar
Orbiter Laser Altimeter (LOLA). LOLA is a science data gathering instrument used for lunar topographical mapping
located aboard the Lunar Reconnaissance Orbiter (LRO) mission. This LRO mission is scheduled for launch sometime
in late 2008. The fiber portion of the array assembly was comprised of step index 200/220μm multi-mode optical fiber
with a numerical aperture of 0.22. Construction consisted of five fibers inside of a single polarization maintaining (PM)
Diamond AVIM connector. The PM construction allows for a unique capability allowing the array side to be "clocked"
to a desired angle of degree. The array side "fans-out" to five individual standard Diamond AVIM connectors. In turn,
each of the individual standard AVIM connectors is then connected to five separate detectors. The qualification test plan
was designed to best replicate the aging process during launch and long term space flight environmental exposure. The
characterization data presented here includes results from: vibration testing, thermal performance characterization, and
radiation testing.
This paper is the first in a series of publications to investigate the use of commercial-off-the-shelf (COTS) components
for space flight fiber laser transmitter systems and LIDAR (laser imaging detection and ranging) detection systems. In
the current study, a hermetically sealed COTS LiNbO3 optical modulator is characterized for space flight applications.
The modulator investigated was part of the family of "High-Extinction Ratio Modulators" with part number MXPE-LN
from Photline Technologies in Besancon, France. Device performance was monitored during exposure to a Cobalt60
gamma-ray source. Results from the testing show little change in device operation for a total accumulated dose of 52
krad.
Exposure of optical materials to transient-ionizing-radiation fields can give rise to transient and/or
permanent photodarkening effects. In laser materials, such as YAG, such induced optical loss can result in
significant degradation of the lasing characteristic of the material, making its selection for optical device
applications in radiation environments unfeasible. In the present work, the ionizing-radiation response of
Nd:YAG laser rods of varying composition and microstructure are examined. The optical properties of the
materials are examined using a variety of optical spectroscopies and observations are correlated with the
results of the ionizing-radiation studies. It is found that radiation damage in these materials is strongly
influenced by the material microstructure.
A firing set capable of charging a 0.05 μF capacitor to 1.7 kV is constructed using a 2.5 mm diameter Series Connected
Photovoltaic Array (SCPA) in lieu of a transformer as the method of high voltage generation. The source of illumination
is a fiber coupled 3 W 808 nm laser diode. This paper discusses the performance and PSpice modeling of an SCPA used
in a firing set application.
Determination of the radiation response of doped-fiber laser materials, systems and components to relevant ionizing
radiation fluxes is central to the prediction of long-term fiber-based laser performance/survivability in adverse and/or
space-based environments. It is well known that optical elements that are placed into orbit around the Earth experience
harsh radiation environments that originate from trapped-particle belts, cosmic rays, and solar events. Of particular
interest to optical materials is the continuous flux of gamma photons that the materials encounter. Such radiation
exposure commonly leads to the formation of color centers in a broad range of optical materials. Such color center
formation gives rise to changes in optical transmission, loss and luminescent band structure, and, thus, impacts long-term
optical device performance.
In this paper we will present the results of our investigation of gamma-radiation-induced photodarkening on the
passive optical transmittance of a number of ytterbium- (Yb-) doped optical fibers. We will discuss the evolution of the
optical response of the fiber across the 1.0 to 1.6 micron wavelength window with increasing gamma exposure. Results
indicate that these fibers exhibit reasonable radiation resistance to gamma exposures typical of a 5-year, low-earth-orbit
environment. Maximum transmittance losses of less than 10% were observed for total gamma exposures of 2-5 krad
(Si).
In this paper we will present the results of our investigation of gamma-radiation-induced photodarkening on the
optical transmittance of a number of ytterbium- (Yb-) doped optical fibers. We will discuss the evolution of the optical
response of the fiber across the 1.0 to 1.6 micron wavelength window with increasing gamma exposure. Results indicate
that these fibers exhibit reasonable radiation resistance to gamma exposures typical of a 5-year, low-earth orbit
environment. Maximum transmittance losses of less than 10% were observed for total gamma exposures of 2-5 krad
(Si).
The use of photosensitive materials for the development of integrated, refractive-index structures supporting telecom, remote sensing, and varied optical beam manipulation applications is well established. Our investigations of photosensitive phenomena in polysilanes, however, have been motivated by the desire to configure, or program, the photonic device function immediately prior to use. Such an operational mode imposes requirements on wavelength sensitivity, incident fluence and environmental conditions that are not typical of more conventional applications of photosensitive material. The present paper focuses on our efforts to understand and manipulate photosensitivity in polysilane thin films under different excitation wavelengths, local atmospheric compositions and thermal history in this context. We find that the photoresponse can be influenced through the control of such optical exposure conditions, thereby influencing the magnitude of the photoinduced refractive-index change attained.
Applications requiring injection of a high-power multimode laser into multiple fibers with equal energies, or specific energy ratios, provide unique design challenges. As with most all systems, engineering trades must balance competing requirements to obtain an optimal overall design. This is particularly true when fabrication issues are considered in the design process. A few of these competing design requirements are discussed in this conceptually simple system. This fiber injection system consists of three components; a refractive beam homogenizer, a diffractive beamsplitter, and a fiber array. We show the design process, starting with first-order design, for an example fiber injection system that couples a high-power YAG laser into seven fibers. Design goals include high efficiency, good beamsplitting uniformity, compact overall size, maximum mode filling of the fibers, and low cost of fabrication and assembly.
Exposure of optical materials to transient-ionizing-radiation fields can give rise to transient and/or permanent photodarkening effects. In laser materials, such as YAG, such induced optical loss can result in significant degradation of the lasing characteristic of the material, making its selection for optical device applications in radiation environments unfeasible. In the present study, the effects of ionizing radiation on the optical response of undoped and 1.1% Nd-doped single-crystal and polycrystalline YAG have been investigated. In the undoped materials it is seen that both laser materials exhibit significant loss at the 1.06 μm lasing wavelength following exposure to a 40 krad, 30 nsec pulse of gamma radiation. In the undoped single-crystal samples, the transmission loss is initially large but exhibits a rapid recovery. By contrast, the undoped polycrystalline YAG experiences an initial 100% loss in transmission, becoming totally opaque at 1.06 μm following the radiation pulse. This loss is slow to recover and a large residual permanent photodarkening effect is observed. Nd-doping improves the optical response of the materials in that the radiation-induced optical loss is substantially smaller in both the polycrystalline and single-crystal YAG samples. Preliminary results on the radiation response of elevated-temperature samples will also be reported.
Access to the requested content is limited to institutions that have purchased or subscribe to SPIE eBooks.
You are receiving this notice because your organization may not have SPIE eBooks access.*
*Shibboleth/Open Athens users─please
sign in
to access your institution's subscriptions.
To obtain this item, you may purchase the complete book in print or electronic format on
SPIE.org.
INSTITUTIONAL Select your institution to access the SPIE Digital Library.
PERSONAL Sign in with your SPIE account to access your personal subscriptions or to use specific features such as save to my library, sign up for alerts, save searches, etc.