Space flight qualification on a novel five-fiber array assembly for the lunar orbiter laser altimeter (LOLA) at NASA Goddard Space Flight Center

Jin, Xiaodan Linda; Ott, Melanie N.; LaRocca, Frank; Chuska, Richard F.; Schmidt, Steve; Matuszeski, Adam; Macmurphy, Shawn L.; Thomes, W. J.; Switzer, Robert C.

doi:10.1117/12.734021

Cited by 7 publications

(4 citation statements)

References 3 publications

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“…Since the quad array (4-fiber) assembly built for the onboard calibration system on ATLAS was a variation on a theme from the Lunar Orbiter Laser Altimeter (5-fiber array), thermal evaluation was necessary to prove that this new array design was viable for flight. [2] Figure 9 includes the thermal induced loss data for the 400 um core FV series fiber in FlexLite™, quad array to fan out assembly as measured real time during thermal cycling for 10 cycles from -20°C to +55°C and 10 cycles from -30°C to +65°C. The data showed thermal induced losses during cold were never higher than 0.15 dB, which is typical for single fiber assemblies not packaged into arrays.…”

Section: Thermal Induced Attenuation Verification Measurementsmentioning

confidence: 99%

“…A two dose rate test was performed to provide data to generate an extrapolation model that could be used to generate data for any dose rate and total dose combination. [2,6] Five tests were conducted for the fiber part types being considered for flight usage. Figure 5 shows an illustration of the test set up for simultaneously capturing real time radiation induced losses in the Cobalt 60 chamber at NASA Goddard Space Flight Center, on all fiber types using 19.6 rads/min and 214 rads/min dose rates.…”

Section: Radiation Induced Attenuation Measurementsmentioning

confidence: 99%

“…The ground support assemblies to test the instrument were fabricated with FV400 for testing the receiver telescope or Nufern 460HP for testing of the instrument signal processing. The fiber system design was based on previous Goddard missions successes such as the Laser Ranging experiment on the Lunar Reconnaissance Orbiter which utilized a 7 fiber array with multiple interconnections and the 5 fiber array used on the Lunar Orbiter Laser Altimeter which utilized a 5 fiber array to fan out assembly [2][3][4][5]. For ATLAS, multiple dual array to fan out assemblies were used to monitor the transmitter and a quad array to fan out assembly for the on board calibration system.…”

Section: Introductionmentioning

confidence: 99%

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The fiber optic system for the advanced topographic laser altimeter system instrument (ATLAS)

et al. 2016

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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.

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Section: Thermal Induced Attenuation Verification Measurementsmentioning

confidence: 99%

Section: Radiation Induced Attenuation Measurementsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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The fiber optic system for the advanced topographic laser altimeter system instrument (ATLAS)

et al. 2016

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“…[1] The custom five-fiber optical cable on LOLA allowed collection of the five individual laser spots in a single telescope and routing to five individual detectors. [2] Both of these systems enabled significant size, weight, and power savings over traditional architectures. Similar improvements using remote placement of the laser source have been difficult due to the inability to reliably transmit high-power optical pulses down a fiber.…”

Section: Introductionmentioning

confidence: 99%

Fiber optic cables for transmission of high-power laser pulses in spaceflight applications

Thomes

Ott

Chuska

et al. 2017

International Conference on Space Optics — ICSO 2010

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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.

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The optical fiber array bundle assemblies for the NASA lunar reconnaissance orbiter; evaluation lessons learned for flight implementation from the NASA electronic parts and packaging program

Ott

Switzer

Chuska

et al. 2017

International Conference on Space Optics — ICSO 2008

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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.

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Space flight qualification on a novel five-fiber array assembly for the lunar orbiter laser altimeter (LOLA) at NASA Goddard Space Flight Center

Cited by 7 publications

References 3 publications

The fiber optic system for the advanced topographic laser altimeter system instrument (ATLAS)

The fiber optic system for the advanced topographic laser altimeter system instrument (ATLAS)

Fiber optic cables for transmission of high-power laser pulses in spaceflight applications

The optical fiber array bundle assemblies for the NASA lunar reconnaissance orbiter; evaluation lessons learned for flight implementation from the NASA electronic parts and packaging program

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