Twelve Channel Optical Fiber Connector Assembly: from ...

Twelve Channel Optical Fiber Connector Assembly: from ...

Fiber Optic Cable Assembly Characterization Studies at NASA Goddard Space Flight Center Melanie N. Ott Sigma Research and Engineering / NASA Goddard Space Flight Center Component Technologies and Radiation Effects Branch [email protected] 301-286-0127 URL: http://misspiggy.gsfc.nasa.gov/tva/authored/fo_photonics.htm The Team: Patricia Friedberg, Matthew Dodson, Shawn Macmurphy, Dan Ginghold, Juan Vela 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight Outline Objectives Qualification performance testing Failure modes and innovative test methods Typical characterization plan Examples: epoxy studies Examples: MTP studies Examples: Cable studies Examples: Radiation studies Conclusions: planned work 02/08/20

NEPP Workshop 2002: Optical C ables for Space Flight Objectives To enable the usage of commerical off the shelf optical fiber interconnection technology for space flight use. To develop innovative test methods to make the path to usage quicker and less expensive. To provide a variety of alternatives to a variety of environments. 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight

Performance Testing and Requirements for Optical Cable Assemblies Thermal cycling Bend test Low and high temperature cable bend Flexibility Impact Accelerated aging Jacket shrinkage Flexure endurance Humidity resistance Cable blocking Freeze test Cable clamping Fluid immersion Cable-to-cable abrasion Jacket tensile strength and elongation Vibration Ambient light susceptability Cable twist bend Cable twist

02/08/20 Insertion loss Return loss Crosstalk Numerical aperture Transmission capacity Attenuation Mating durability

Fungus Toxic hazard, Odor, Flammability Vacuum stability Atomic oxygen Solar UV radiation Plasma Ionizing radiation ESD Thermal shock Strippability Crush resistance Strength testing NEPP Workshop 2002: Optical C ables for Space Flight Technology Validation What do I validate this technology? Failure modes study What approach do I take? System type approach to the assembly How? System analysis (materials, design,compatibilities etc) Characterization plan that takes into account the greatest number of failure modes for space flight. Design innovative testing methods to expedite validation 02/08/20

NEPP Workshop 2002: Optical C ables for Space Flight Failure Modes and Testing Failure or degradation Condition mode Validation Method Optical materials/materials changes Vacuum, temp, aging Analysis, thermal cycling, vacuum testing. Attenuation from environment Temp, radiation Analysis, Radiation exposure Thermal cycling, Materials shrinkage

Aging, temp Thermal cycling Cracking Temp, vibration, handling, design, termination process Thermal cycling, vibration, analysis 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight Characterization Plan Materials analysis and test, Termination validation as a system. Thermal vacuum use configuration when possible. Thermal cycling, long dwell at extremes, 1 C/min to extent of specification, -20C to +85 C for COTS, -55C to +125C for Space, 40 cycles, 25 30 minute soak, 1 or 2 C/min rate. Vibration testing, Random vibration to protoflight levels, Verified survival and operational ability during launch using typical

launch parameters ~ 14.1 grms total for protoflight small box components. 3 minutes per axis, 20 grms total Radiation analysis and test. Two dose rate test and extrapolate to environment Space flight environments from GSFC are less than 1 rad/min and more typically less than .1. 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight Materials Characterization Through analysis, identify COTS materials without heritage (epoxy, coating, etc) for use in space assembly. Validate through termination process as a system, (cure for epoxy, strip test for coatings, visual, optical performance.) Validate through test methods, Thermal (array connector ), ASTM-E595 ASTM-E595 in assembly configuration (simplex connector). ASTM-E595 in cable configuration (coating material with and without connector). 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight

Epoxy Studies Tracon BA-253 only fiber optic epoxy Tested AngstromBond AB9119, 9112 in configuration and out, AB9119 passed using ASTM-E595. MTP connector assembly, epoxy not approved for flight MTA-022, BA-253 failed termination study for use on MTP. Evaluation through termination and test of new epoxy AB9320. If AB9320 passes, next use ASTM-E595 to verify that the epoxy will not outgass and will be compatible with system. 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight MTP Assemblies Studies MTP array connector with 12 optical fiber ribbon cable, - 62.5/125/250 micron, commercial system. - 100/140/250 micron, spaceflight system. - Termination study X Y 02/08/20 Z NEPP Workshop 2002: Optical C ables for Space Flight

MTP Characterization ; 100/140 space flight vibration test Vibration Test Results: DUT B, Y Axis Optical transmission for MTP DUT B during Y axis vibration testing 0.300 37 34 31 28 25 22 -0.100 19 Ch 5 16 0.000 13 Ch 3

10 0.100 7 Ch 1 4 0.200 1 Optical transmission (dB) 0.400 Ch 8 -0.200 Ch 10 -0.300 Ch 12 -0.400 -0.500 Data point (~ 5 sec/point)

02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight MTP Termination Study 62.5/125 MTP assembly study: found failures related to termination process. During process, cracking Epoxy alternatives necessary for 100/140 version. Currently conducting a study on process and epoxy Curing, Visual, Optical Performance, Thermal Cycling, ASTM-E595 on alternative epoxy 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight Cable Studies % Shrinkage % Shrinkage of cable jacketing vs. thermal cycle, sample set 1 2.20 2.00

1.80 1.60 1.40 1.20 1.00 0.80 0.60 0.40 0.20 0.00 -0.20 0 FON1004 OC1614 OC1008 H06 HL1 8 16 24 32 40 48

56 64 72 80 Thermal Cycle -55C to +125C, 20 min dwell at extremes, 2 C/min 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight Radiation Studies MTP Assembly 4 rads/min & 27 rads/min at +25 C, 1300 nm 5.24 m with mated pair. A(D) = 7.47*10-4 .1993 D.8007 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight

Radiation Studies: Actual Data Commercial 62.5/125/250 OFS Fitel Collected Data 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight Radiation Studies: Extrapolation Radiation induced attenuation -25 C, 1, .1 & .01 rad/min extrapolated 1.4 Radiation induced attenuation (dB/m) 1.2 1 rad/min 1 0.1 rad/min 0.8 .01 rads/min 0.6 0.4 0.2

0 0 1 2 3 4 5 6 Total dose (rads) 7 8 9 10 4 x 10 Commercial 62.5/125/250 OFS Fitel Extrapolated Data for -25C 02/08/20 NEPP Workshop 2002: Optical C

ables for Space Flight Planned Work MTP twelve channel array connector and optical fiber ribbon cable Termination study Alternatives to epoxy, materials study Diamond AVIMS characterization for space flight Radiation: Optical fiber database for space flight environments. http://misspiggy.gsfc.nasa.gov/tva/authored/fo_photonics.htm http://www.nepp.nasa.gov/ This work is funded by NEPP Packaging Project & Electronics Radiation Characterization Project 02/08/20 NEPP Workshop 2002: Optical C ables for Space Flight

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