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.
The Lunar Reconnaissance Orbiter
The LRO is the first in a series of missions towards the exploration of the Moon and Mars for the purpose of providing remote human habitat bases for planetary study. LRO will do extensive mapping of the lunar surface in search of the most appropriate landing sites. The LRO instrument suite will identify resources and explore the environment. High-precision mapping of the moon is a requirement for any future lunar landings. Dr. Farzin Amzajerdian of NASA Langley Research Center points out in his recent article published in Photonics Spectra, “Even though Apollo missions targeted well-surveyed landing sites, they still experienced some close calls”. In fact, on page 55 of the 2008 Photonics Spectra July issue, Dr. Amzajerdian illustrates just how close the Apollo 14 lunar landing came to a small crater, only inches away from one of its support structure legs. Therefore, the goal of the Lunar Orbiter Laser Altimeter (LOLA), an instrument included in the suite of instruments on LRO, will provide a 3-dimensional mapping of the lunar surface topography for accurate and safe location of future landing sites. LOLA will use a 1064 nm pulsed laser to perform the required altimetry measurements.
The Longest Laser Link in Space
During the conceptual design of the LOLA instrument, an experiment with the Mercury Laser Altimeter (MLA) Instrument in May 2005, that had launched in 2004, provided the assurance that laser communications could traverse long distances through space. A laser system built and designed at GSFC called “HOMER”  located at NASA Goddard’s Geophysical and Astronomical Observatory was used to contact the MLA aboard MESSENGER on its way to Mercury. This experiment established a ranging link across 24 million kilometers, the longest laser link to have ever been performed in space. [4,5].
The Lunar Orbiter Laser Altimeter and Laser Ranging
The MLA experimental results were so promising that the Principal Investigators, Dave Smith of NASA and Maria Zuber of MIT, decided that LOLA would not only perform topography mapping of the Moon but would simultaneously make ranging measurements from the Earth while orbiting the moon on LRO, with some instrument enhancements and an optical fiber link. This enhancement would be called the “Laser Ranging” mission for LRO and would use a pulsed 532 nm Earth-based laser from the station at Goddard’s facility to LOLA to collect high-precision distance information using the timing of firing-to-receiving at the LOLA instrument. The challenge was to receive the laser pulses with the Laser Ranging Telescope (LRT) located on the end of High Gain Antenna System boom arm while it was pointing at the Earth and transmit the information across 3 subsystems to one of the LOLA detectors. This had to be conducted with a compact but multi-optical fiber configuration. The challenge of the LOLA instrument system was to reduce the size and weight of the previous MLA hardware design from four telescopes into one telescope with the help of a fiberbased array precisely compressed into a single connector.
Where the MLA instrument consisted of four telescopes and was designed to be capable of measuring with a 0.5 m precision, LOLA consists of only one telescope and was designed to produce 0.1 meter precision. Both instruments were designed to measure the planetary reflection timing as a result of firing the short duration pulsed 1064 nm laser aboard. LOLA uses a diffractive optical element on the transmitter to split a single laser beam into five separate beams. On the receiver optics end, a precisely positioned optical fiber array, behind the receiver optics, links each beam to a separate detector. The time-of-flight measurements will provide ranging information. The pulse spreading of the reflected beam will provide information on surface roughness, and the energy of the returned beam will provide surface reflectance. The five spots will provide slopes along and across the orbit track. In addition, to accommodate the “Laser Ranging” from Earth, LOLA detector channel one will be used to monitor the ranging signals from the 532 nm pulsed laser located at the Greenbelt facility. Fig. 2 shows an artist’s rendition of the LRO space craft configuration and the LOLA instrument.
For each of the ranging and altimetry applications, the requirement was that a single array connector be used to couple light from each of the receiver telescopes. Early in development, a modified Diamond AVIM connector was chosen due to its longstanding space flight heritage, a heritage that began with Lockheed-Martin in the 1990s for single mode applications and continued with its usage on the ICESAT Geoscience Laser Altimeter system (GLAS), the Shuttle-Return-to-Flight high definition heat tile sensor camera, and the Mercury Laser Altimeter. For LOLA, Polymicro’s 200/220 micron step index FI series optical fiber was chosen to meet the optical performance requirements, and the 400/440 micron step index FV series optical fiber was chosen for the “Laser Ranging” (LR) application. For LOLA, the requirements dictated five optical fibers be held into a precise alignment pattern with tight tolerances and for LR application, seven fibers were used to provide optimal optical transmission and enhanced reliability.
LOLA Optical Assembly Design
The solution to the LOLA challenge is pictured in Fig. 3, a five fiber array on side A, fanned out to individual standard AVIM connectors on side B. The largest challenge was machining and packaging the pattern on the array side connector ferrule. The tight hole tolerance had to be balanced with the packaging of the fibers into the holes. That is not to say that the termination process was easy; it was indeed not. The process was arduous and time-consuming, with a 50% yield at best once all tests and polishing procedures had been performed. No voids in the epoxy or defects of any kind would be acceptable for these unique space flight assemblies. The ferrules themselves were bought as blanks from Diamond USA/Switzerland and custom drilled in the NASA GSFC Mechanical Systems Engineering Division, Code 540.
In addition to positioning requirements, the LOLA assembly also had very precise length requirements. Each fiber on the fan out side required a different path to its designated LOLA detector, and the detectors were spread around the instrument perimeter. Both for Laser Ranging and LOLA applications, a larger diameter AVIM connector would be required for long-term reliability of the array termination strain relief. For example, the connector spring needed to be enlarged to accommodate the large fibers with the acrylate coating still on. Acrylate coatings are preferred due to the ease of removal with methylene chloride, and chemical stripping is required for space flight terminations. Any scoring or scratching due to tooling could result in latent failure modes that cannot be fixed once the space instrument is launched.
LOLA Manufacturing and Qualification
The termination procedures used were screened with rigorous requirements validation testing with in-situ transmission monitoring during survival level environmental exposure. The screening details and results are in . One of the significant lessons learned was related to the vibration levels used for the requirements validation. Early on, the only available information regarding the system-level vibration expectations was through knowledge of the launch vehicle and the appropriate profile as chosen by GEVS. Once the flight hardware was built, the mechanical random vibration levels were larger than expected. The instrument team requested that protoflight testing – meaning testing on the actual flight articles prior to delivery to the instrument – would be required due to the new design and the elevated vibration levels. In past history, most flight hardware was tested for thermal workmanship levels but not always vibration. In this case, thermal vacuum testing was conducted for eight cycles and two-hour soaks at the extremes with the ramp rate at 30 degrees per hour followed by a random vibration test. Once integrated with the LOLA, the flight articles were vibration and thermal vacuum tested again to instrument set levels. Once LOLA integrated with the entire LRO space craft once again, the assemblies endured vibration and thermal to the space craft thermal and vibration level requirements. So the LOLA integration flight assembly, as a proto-flight article, endured three vibration tests and three thermal vacuum qualification tests.
During manufacturing, screening and qualification, the procedures were drafted into a flow and list of documents for quality controlling the repeatability of the product production. The flight delivery flow is in Fig. 4.
As is common practice with all flight assemblies , all cables made of fluoropolymers and all connector boots must pass ASTM-E595 as an initial screen and are put through thermal preconditioning. For the hytrel boots on the LOLA assemblies, the preconditioning involves a high-temperature vacuum bake out to ensure compliance to ASTM E595 post processing, and for cables the preconditioning procedure involves thermal cycling in ambient with hour-long soaks at the hot extremes and a half an hour at a cold temperature ~-30 °C. The survival upper limit requirement for the subsystem is used as the hot thermal extreme during thermal preconditioning, and the cycling is ramped at 1 to 2 °C/minute for anywhere between 40 to 70 cycles, depending on the cable type. For LOLA, the preconditioning was conducted for 50 cycles using the upper survival thermal limit. Assembly pieces are cut to approximately the length that will be used to maximize the effectiveness of the thermal preconditioning procedure.
LOLA Bundle Fiber Assembly Quality Documentation
The LOLA bundle assembly included a special mechanical adapter to couple the light from the receiver optics to the bundle array. It was imperative that the clocking be exact such that the reflected five beam image from the lunar surface would align with the fiber array for the highest transmission possible. The clocking of the array was performed visually under a microscope at 200X magnification such that mating to the adapter would be simple. The adapter held the array in a position of 25 microns back from the end of the adapter interface to the receiver optics. The flight adapters ended up on the tight side of the dimensional tolerance, which caused the adapter to fit too tightly on the connector ferrules. Anomaly investigations were performed and proved that the stainless steel ferrules were causing metallic burrs on the tightly toleranced adapter holes, and this resulted in misalignment and difficulty in mating and demating without damage to the arrays. Once the assemblies were properly mated to the adapters, they were not removed. Rigorous processes were put in place to ensure the safety of the unique flight bundle assemblies. The array strain relief was investigated for integrity, and a ferrule compression test was added to the manufacturing procedures to ensure the quality of each array assembly. The compression screen test provided a higher quality on the final product than would be achieved with only the thermal vacuum workmanship testing alone. Fig. 5 includes the list of documentation to ensure the quality of the manufacturing, testing and integration of the LOLA bundle array assemblies.
LOLA Documentation for Configuration Management
|Document Name||CM Documentation Number|
|LOLA Fiber Optic Flight Assemblies||LOLA-OPTICS-WOA-0338|
|Thermal pre-conditioning on Flexlite 200/220 μm fibers for flight application||562-PHOT-WI-LOLA-TP-001|
|Preconditioning Procedure for AVIM Hytrel Boots for LOLA fiber optic assemblies||562-PHOT-WI-LOLA-VAC-001|
|Procedure for Diamond AVIMS PM Kit Pre-Assemble Inspection||LOLA-PROC-0104|
|Assembly and Termination Procedure for the Lunar Orbiter Laser Altimeter Five Fiber Custom PM Diamond® AVIM Array Connector for the Lunar Reconnaissance Orbiter||LOLA-PROC-0098|
|Insertion Loss Measurement Procedure For LOLA 5-Fiber Assembly (Open Beam Configuration)||562-PHOT-WI-LOLA-IL-001|
|Integration of the LOLA Fiber Optic Bundle to the Telescope Adapter||LOLA-PROC-0140|
|LOLA Fiber Bundle Inspection and Test Procedure||LOLA-PROC-0099|
Once all testing was performed and the assemblies accepted for flight, they were rinsed in isopropyl alcohol to reduce the contamination of the assembly to other parts of the flight instrument suite. Contamination for LOLA was a concern due to the location of the instrument on LRO. Nearby would be an instrument that would be functioning in the UV spectrum where contamination is much more of a problem for the optical systems. Darkening of the optical surfaces can occur from any residues that outgas from nonmetallic materials and condense on the smooth optical interface surfaces. This is the single most common failure mode among laser systems.
LOLA Optical Fiber Bundle Array Integration
Several fit checks were performed on the LOLA engineering mock up such that when flight integration time arrived, the flight hardware would fit exactly to the instrument configuration. Integration of the flight hardware occurred in October of 2007. The pictures in Fig. 6 show the integration of the flight optical fiber bundle array assembly to the LOLA flight instrument.
The Laser Ranging Application
The Laser Ranging assemblies proved much more challenging than the LOLA optical fiber bundles. The main reason was due to the necessity for traversing 3 subsystems which included the boom arm of the High Gain Antenna System, the HGAS gimbals used to steer the antenna, and the long run across the space craft over to the LOLA detector on the opposite end of the space craft. For ease of integration, it was necessary for three cables to complete this set, which implied two optical fiber array-to-array interconnections in precise clocked alignment.
Fig. 7 shows the concept as drafted by System Instrument Manager Ronald Zellar during Engineering Peer Reviews for Laser Ranging on LRO and presented at the Laser Ranging Workshop by Dave Smith in 2006. The signal from the Earth is received by the Laser Ranging telescope and routed over from the High Gain Antenna, through the gimbals, down the boom, around a deployment mandrel and over to the LOLA detector channel 1.
In Fig. 8, the complexity of the fiber route is represented with greater detail. Since subsystems integration would be complicated and challenging for scheduling, a requirement was set for an interconnection point between gimbals 1 and 2 and another where the entire High Gain Antenna System linked to the space craft on LRO.
Development of Laser Ranging Application Optical Fiber Bundle Array Assemblies
The Laser Ranging assemblies were designed for enhanced reliability, flexibility and stable performance over a very wide thermal range. Originally, the thermal requirement for the cold limit was -75 °C. Add the cold thermal extreme with all the motion expected from the coiling and uncoiling that occurs inside of the gimbal cable wraps and the deployment hinge and it’s clear that to couple enough light reliably would require more than fiber. The optics team chose seven optical fibers at 400/440 microns to provide optimal optical performance while maintaining mechanical flexibility. The ferrules were a concern because again, as with LOLA, the pattern for the fibers had to be precisely centered and within a tight tolerance to be mated to another assembly and minimize the insertion loss.
The largest challenge the team faced was to go from concept to flight hardware in less than two years. The AVIM connector modifications: a larger size to accommodate the large size fibers and clocking ability like polarization maintaining connector predecessors. Diamond Switzerland, along with the Mechanical Systems Division efforts led by Adam Matuszeski at Goddard Space Flight Center, worked the challenges of making the new customized PM AVIM successful. During engineering prototyping, the ferrule material was changed from stainless steel 303 to stainless steel 416 to better accommodate the thermal requirements. Neither of these material types were used with the commercial AVIM connectors, but for ease of the fiber pattern drilling it was the necessary choice to meet the schedule. The custom ferrule drilling was performed both by NASA Goddard and by Diamond Switzerland. For the flight models, the Diamond Switzerland ferrules were used. Fig. 9 illustrates the endface pattern and custom drill “flower” pattern.
The optical performance requirements were difficult to meet. Initially, losses at the interconnection locations were complicated by the endface concave polishing conducted such that the arrays would not be in physical contact while real time clocking optimization was performed. The actual adapters used to perform clocking optimization were purposely gapped to avoid any issues with contamination causing gouging or cracking of the optical fiber array during this process. Originally, the low-profile standard AVIM adapter was chosen, but after mechanical difficulties similar to those experienced on LOLA, the Diamond “Cleanable” adapter was used for its ceramic insert that did not experience the scoring that was experienced using a stainless ferrule with the low-profile adapter. In addition, particulates would collect inside of the adapters with repeated mating, and therefore the “Cleanable” version (which could be separated into two parts) was the better choice.
The bundle cable was manufactured to fit the existing cable wraps in gimbal design such that no risk would result from putting an optical fiber harness into the gimbal systems. Considerable effort went into designing the engineering model assemblies to avoid known failure modes and tested with in-situ optical transmission monitoring where possible for:
• Array Compression
• Thermal Vacuum Workmanship, 8 cycles
• Random Vibration Launch Conditions
• Thermal Cycling (accelerated life)
• Cold Gimbal Motion Testing, 20,000 Mechanical Cycles with Active Monitoring
• Gimbal Life Testing, 20,000 Motion Cycles
• Gamma Radiation Exposure
Reference  contains the bulk of the data collected on the engineering models that paved the way for the documentation list for the flight bundle assemblies. The list of quality documentation and procedures is presented in Table 2.
Laser Ranging Procedures and Quality Documentation
|Document Title||Document Number|
|Thermal Pre-conditioning on Flexlite 200/220 µm fibers for flight application||LOLA-PROC-0137|
|Preconditioning Procedure for AVIM Hytrel Boots for LOLA fiber optic assemblies||LOLA-PROC-0138|
|Diamond AVIM PM Kit Pre-Assembly Inspection||LOLA-PROC-0104|
|Ferrule Polishing & Ferrule/Adapter Matching Procedure||LOLA-PROC-0139|
|Assembly and Termination Procedure for the Laser Ranging Seven Fiber Custom PM Diamond AVIM Array Connector for the Lunar Reconnaissance Orbiter||LOLA-PROC-0112|
|Compression Test Procedure for Fiber Optic Connector||LOLA-PROC-0141|
|Active Optical Power Optimization Procedure for The Laser Ranging Optical Fiber Array Assemblies||LOLA-PROC-0110|
|Laser Ranging Fiber-Optic Bundle Optical Test Procedure||LOLA-PROC-0107|
|Insertion Loss Measurement Procedure for The Laser Ranging Optical Fiber Array Bundle Assemblies||LOLA-PROC-0111|
|Mating of Two LR 7-Fiber Optical Fibers Using Cleanable Adapter||LOLA-PROC-0142|
|Cutting Back The Kynar Strain Relief For Integration||LOLA-PROC-0143|
|Fiber Optic Bundle Inspection and Insertion Loss Measurement||LOLA-PROC-0148|
Several anomalies were investigated during the course of the development from the engineering models to the flight models, and as a result the jacketing was removed from immediate contact with the connector. Fig. 10 shows the final configuration of the Laser Ranging cable set that was approximately 10 m in length.
Integration of the Laser Ranging Assemblies
Integration took approximately 9 months and was challenging as expected. Some subsystems were being assembled simultaneously, which made having the necessary resources on hand to accomplish the testing at each location a difficult task. The integration and testing lead, Joanne Baker, made the job much less arduous by keeping the schedule as flexible as possible. The optical fiber assemblies were arranged as such.
Fiber Optic Bundle (FOB) designations and integration locations.
|Optical Assembly||Subsystem Link|
|FOB 1||Laser Ranging Telescope, through Gimbal 1, to the bracket between Gimbals 1 and 2.|
|FOB 2||Bracket between Gimbals 1 & 2, through Gimbal 2, down the boom, and around the deployment mandrel.|
|FOB 3||Bracket for the High Gain Antenna System to Detector 1 on LOLA.|
The Laser Ranging system was integrated in the following order:
1) FOB 2 integrated into Gimbal 2 cable wrap and looped onto boom section.
2) FOB 1 integrated into Gimbal 1 cable wrap.
3) FOB 1 & 2 interconnected with gimbals 1 and 2 were combined, partial boom segment.
4) FOB 2 integrated completely to completed boom and deployment mandrel.
5) Gimbals/Boom integrated to the High Gain Antenna.
6) LR telescope integrated to High Gain Antenna and connected to FOB 1.
7) FOB 3 integrated to Instrument Panel, extra looped aside in preparation for LOLA integration.
8) FOB 3 integrated to other side of LRO space craft.
9) LOLA integration.
10) FOB 3 interconnected to LOLA.
11) HGAS integrated to LRO space craft
12) FOB 3 interconnected to FOB 2 at LRO space craft bracket.
Before and after every integration operation, optical transmission was monitored and compared to the system level allocations set by lead fiber optics engineer Melanie Ott. Motion testing was run in-situ to monitor performance in the cable wraps of each gimbal during integration. Any exposed cables on the space craft were covered with conducting tape for thermal control such that the cold thermal survival limit could be maintained at -55°C.
System Integration Results
Previously mentioned in section 2.7 was the list of integration steps taking through out the process of assembling the Laser Ranging system to the LRO and LOLA. At each step in the process, insertion loss measurements were made to ensure the safety and proper handling of the optical fiber assemblies. In table 4 the system allocations for insertion loss as set by the lead fiber optics engineer, Melanie Ott were compared to the as measured quantities collected during flight integration. The allocations and measurements in Table 4 do not include packing fraction losses as a result of the gaps and cladding between the seven fibers for light collection.
System Allocations vs. Actual Measured Insertion Loss Measurements During LRO Integration for FOB 1& 2.
|Subsystem Item||Analysis Allocation Insertion Loss dB (%loss)||Actual Measured Insertion Loss||Comments|
|Maximum optical bench insertion loss (unstressed)||< 2.18 dB (39.5%)||1.45 dB (28.3%)||Includes two interconnections points with AR coatings and optical fiber cable losses|
|Routing Losses FOB 1 & 2||1.0 dB (20%)||1.6 dB (30.1%)||higher losses expected from gimbals, losses were larger due to more bends than original design.|
|Gimbal Motion||0.3 dB to 0.6 dB (6.7% to 12.9%)||0.18 dB (4%) change||Change in insertion loss over 180 degree motion|
|Total Integrated FOB 1& 2||~3.18 dB (52%)||3.05 dB (50.4%)||Final Measurement for HGAS|
Once the first two assemblies were integrated, the final measurements indicated that the team was able to keep the total insertion loss of the most challenging part of the routing to under the system level allocated amount by .13 dB. Table 5 lists the expected and measured losses for the entire set of assemblies FOB 1, 2 & 3 as integrated and completely connected from the LR telescope to the detector at LOLA.
System Allocations vs. Actual Measured Insertion Loss Measurements Post Integration Completion
|End Product Subsystem Item||Analysis Allocation Insertion Loss dB (%loss)||Actual Measured Insertion Loss||Comments|
|Packing Fraction Loss by design||1.65 dB (31.6%)||N/A||Losses from gaps for light transmission based on potential light transmission|
|Routing Losses FOB 3||0.5 dB||Losses allocated to the routing of FOB 3 across LRO from HGAS to LOLA.|
|Total IL from FOB 1 & 2 Routed into HGAS||3.18 dB||3.05 dB||Change in insertion loss over 180 degree motion|
|Mating/Demating Variation||0.14 dB|
|Total Post Integrated||5.47 dB||4.0 dB||Final measured for FO system|
|Total Post Integration Transmission||28.4 %||39.7%||Within allocation|
The full system was measured for insertion loss with HGAS integration completed to the LRO on June 14, 2008 and the final results are in the last row of Table 5. The system met the requirements for performance. Since then several system level tests have been performed on the LR and LOLA system with nominal results. The full integration of LRO is now complete and proceeding through a long list of space craft and instrument level tests.
Presented here was the journey of developing and integrating the optical fiber assemblies for the Lunar Reconnaissance Orbiter. The array assemblies developed for this space flight mission application are unique in the world. The LRO will be launching in April of 2009 and will perform extensive mapping of the Moon, and the laser ranging information will help provide information to enhance the existing gravity model. For more information, please consult the websites, http://nepp.nasa.gov, and http://photonics.gsfc.nasa.gov.
The authors would like the thank the following people for their support in making this project and paper a success: Adam Matuzseski, Mark Flanegan, Michael Mulloney, Matt Showalter, Steve Schmidt, Luis Ramos-Izquierdo, John Cavanaugh, Marcellus Proctor, Jelila Mohammed, Ron Zellar, Glenn Jackson, Joanne Uber, Joanne Baker, Kusum Sahu, Henning Leidecker, Patricia Friedberg, Denise Radliff, Bruce Meinhold, Rick Jacobs, Steven Brown, Gordon Casto, Ken LaBel and Mike Sampson (NEPP program managers), Craig Tooley and Cathy Peddie (LRO Program Managers).
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