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.
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.
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.
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.
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.
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.
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.
In the past year, a unique capability has been created by NASA Goddard Space Flight Center (GSFC) in support of
Lunar Exploration. The photonics group along with support from the Mechanical Systems Division, developed a seven
fiber array assembly using a custom Diamond AVIM PM connector for space flight applications. This technology
enabled the Laser Ranging Application for the LRO to be possible. Laser pulses at 532 nm will be transmitted from the
earth to the LRO stationed at the moon and used to make distance assessments. The pulses will be collected with the
Laser Ranging telescope and focused into the array assemblies. The array assemblies span down a boom, through
gimbals and across the space craft to the instrument the Lunar Orbiter Laser Altimeter (LOLA). Through use of a LOLA
detector the distance between the LRO and the Earth will be calculated simultaneously while LOLA is mapping the
surface of the moon. The seven fiber array assemblies were designed in partnership with W.L. Gore, Diamond
Switzerland, and GSFC, manufactured by the Photonics Group at NASA Goddard Space Flight Center (GSFC) and
tested for environmental effects there as well. Presented here are the requirements validation testing and results used to
insure that these unique assemblies would function adequately during the Laser Ranging 14-month mission. The data
and results include in-situ monitoring of the optical assemblies during cold gimbal motion life-testing, radiation,
vibration and thermal testing.
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