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March 30, 2004 NASA Goddard Space Flight Center
Optical Assemblies for Space Environments: Characterization of W.L.Gore Flexlite with Diamond AVIMS
for Space Flight Environments
Melanie N. Ott
Sigma Research and Engineering/
NASA Goddard Space Flight CenterMore information: 301-286-0127, [email protected]
URL: nepp.nasa.gov/photonics
misspiggy.gsfc.nasa.gov/photonics
March 30, 2004 NASA Goddard Space Flight Center
Optical Assemblies for Space Environments: Characterization of
W.L.Gore Flexlite with Diamond AVIMSfor Space Flight Environments
Melanie N. Ott
Sigma Research and Engineering/
NASA Goddard Space Flight CenterMore information: 301-286-0127, [email protected]
URL: nepp.nasa.gov/photonics
Technical Team: Shawn Macmurphy, Marcellus Proctor, Patricia Friedberg
March 30, 2004 NASA Goddard Space Flight Center
Photonics Manufacturing and Testing LabParts, Packaging and Assembly Technologies OfficeNASA GSFC, Code 562
March 30, 2004 NASA Goddard Space Flight Center
Outline• MLA Requirements & Components
• Characterization plan
• Materials Study Results
• Vibration Testing & Results
• Thermal Testing & Results
• Radiation Parameters
• Radiation Testing Results
• Conclusions
March 30, 2004 NASA Goddard Space Flight Center
MLA Requirements• Large diameter optical fiber, 200 and 300 micron, NA of .22 for use at 1064 nm.
• High performance assembly;
• Low insertion loss (< 0.4 dB)
• Repeatability.
• Stability in harsh environment
- thermal, vibration and radiation.
• Non-outgassing components.
• Assemblies 26.1 inches long used for beam delivery system, not interconnected.
Parts selection to meet requirements: • Diamond AVIMs with custom ferrule drilling, D-6201.1
• Part # E070040095VNAS1 Ferrule custom drilled for 220 fiber.
• Part # E070040095VNAS2 Ferrule custom drilled for 330 fiber.
• Part # 070015048V001, Hytrel boots.
• W.L.Gore, Flexlite simplex cable, FON1173, FON1174
• Polymicro Technologies optical fiber,
• FIA200220500, 200 micron, acrylate, .22 NA, step index
• FIA300330500, 300 micron, acrylate, .22 NA, step index
• Epoxy, Epo-Tek 353ND.
March 30, 2004 NASA Goddard Space Flight Center
AVIMs and Flexlite AssemblyTerminations performed to NASA-STD-8739.5 and procedure 562-WI-8700.2
March 30, 2004 NASA Goddard Space Flight Center
Mercury Laser Altimeter
March 30, 2004 NASA Goddard Space Flight Center
Characterization Plan All testing conducted: recorded before and after optical performance data
as well as in-situ optical data.• Vacuum Outgassing,
– All materials must pass ASTM-E595. • Vibration Induced Effects
– Verified survival and operational ability during launch using typical launch parameters for small box components.
– 3 minutes per axis, 14.1 grms total, 3 assemblies tested.• Thermal Induced Effects
– -30°C to +50 °C, 90 cycles, last 42 monitored, (tests are conducted at 10°C higher than expected environmental extremes).
– 25 minute soak, 2 °C/min ramp rates.• Radiation Effects
– Space flight environments from GSFC are less than 1 rad/min and more typically less than 0.1 rads/min. Two dose rates used to possibly provide a model for extrapolation to lower dose rates.
• 11.2 rads/min for lower dose rate, 22.7 rads/min for higher dose,• Up to 30 Krads while maintaining a cold temperature of –20° C. • Actual projected dose rate for MLA: 16.44 rads/day, .685 rads/hour, .011 rads/min
March 30, 2004 NASA Goddard Space Flight Center
Materials Results, nonmetallic parts
• Cable- Flexlite passed when tested previously in configuration during development of ICESAT (GLAS) with acrylate coated fiber.
- Cable does require preconditioning for thermal stability 8 cycles, 60 min @ 60°C, 25 min @ -20°C, < 2°C/min
• Connector BootsHytrel 8068 require de-gas preconditioning, 102 to 1 Torr, 140°C, 24 hours.Once preconditioned, ASTM-E595 results were:0.48 % TML, 0.10% CVCM.
• EpoxyEpoTek 353ND is contained in GSFC outgassing database.
March 30, 2004 NASA Goddard Space Flight Center
Cable Designations and Initial Visual Inspection
Assembly Code Side A Side B
MP1
MP2
MP3
Pre-environmental Testing Visual Inspection
MPX Test assemblies were made of two AVIMS/AVIMS interconnected with an AVIMS adapter, each ~ 24 inches long.
Presented above are end face pictures of the mated sides that were exposed to environmental testing
March 30, 2004 NASA Goddard Space Flight Center
Vibration Testing
3 minutes/axis, 14.1 grms total, 3 axis test
X
Y ZZ axis orientation X axis orientation
March 30, 2004 NASA Goddard Space Flight Center
Vibration Parameters for Test
Frequency (Hz) Protoflight Level
20 0.026 g2/Hz
20-50 +6 dB/octave
50-800 0.16 g2/Hz
800-2000 -6 dB/octave
2000 0.026 g2/Hz
Overall 14.1 grms
Random Vibration Profile ParametersBased on EO-1 and MLA specifications
3 minutes/axis, 14.1 grms total, 3 axis test for mated pair
March 30, 2004 NASA Goddard Space Flight Center
Vibration Test Results: X axis MP1
Optical Losses During X axis Vibration Test on MP1
-5.000E-04
0.000E+00
5.000E-04
1.000E-03
1.500E-03
2.000E-03
2.500E-03
3.000E-03
3.500E-03
1 92 183
274
365
456
547
638
729
820
911
1002
1093
1184
1275
data point
Inse
rtio
n L
oss
(d
B)
MP1-Xaxis
March 30, 2004 NASA Goddard Space Flight Center
Vibration Test Results: Y axis MP1
Optical Losses During Y Axis Vibration Test on MP1
-5.0000E-04
0.0000E+00
5.0000E-04
1.0000E-03
1.5000E-03
2.0000E-03
2.5000E-03
1 85 169
253
337
421
505
589
673
757
841
925
1009
1093
1177
Data point
Inse
rtio
n L
oss
(d
B)
MP1-Yaxis
March 30, 2004 NASA Goddard Space Flight Center
Vibration Test Results: Z axis MP1
Optical Losses During Z Axis Vibration Test for MP1
-1.000E-03
-5.000E-04
0.000E+00
5.000E-04
1.000E-03
1.500E-03
2.000E-031 82 163
244
325
406
487
568
649
730
811
892
973
1054
1135
Data point
Inse
rtio
n L
oss
(d
B)
MP1-Zaxis
March 30, 2004 NASA Goddard Space Flight Center
Vibration Test Results Summary
Assembly Set
Vibration Test Axis
Max Induced Insertion Loss
Final Change in Insertion Loss Post
Testing
MP1 X 0.0031 dB 0.0028 dB
MP1 Y 0.0024 dB 0.0012 dB
MP1 Z 0.0015 dB 0.0006 dB
MP2 X -0.0002 dB* -0.0027 dB *
MP2 Y -0.0006 dB* -0.0012 dB *
MP2 Z 0.0027 dB 0.0004 dB
MP3 X -0.0005 dB* -0.0017 dB *
MP3 Y 0.0004 dB 0.00 dB
MP3 Z 0.0003 dB* -0.002 dB **Indicates an increase in power post vibration testing
No endface damage was detected during post vibration visual inspection.
March 30, 2004 NASA Goddard Space Flight Center
Thermal Testing -30°C to +50 °C, 90 cycles, last 42 cycles monitored optically.
Program malfunction caused lack of data collected during the first 48 cycles.
March 30, 2004 NASA Goddard Space Flight Center
Thermal Testing ResultsInsertion Loss for MP1 During 42 Thermal Cycles
vs. Time
-6.00E-02
-4.00E-02
-2.00E-02
0.00E+00
2.00E-02
4.00E-02
6.00E-02
8.00E-02
1
628
1255
1882
2509
3136
3763
4390
5017
5644
Time (min)
0 100 200 300 400 500 600 700 800 900 1000-0.04
-0.03
-0.02
-0.01
0
0.01
0.02
0.03
0.04
0.05
Ins
ert
ion
Lo
ss
(d
B)
Time (min)
0 100 200 300 400 500 600 700 800 900 1000
-30
-20
-10
0
10
20
30
40
50
60
Te
mp
era
ture
(d
eg
ree
s C
)
Time (min)
Insertion Loss of MP1 with Temperature vs. Time for 7 cycles
Insertion loss for MP1During 68th to 75th cycle (Red) with temperature (Black). Insertion loss increases with decreasing temperature.
Example of data collected for all assembliesMP1 during 42 cycles (after initial 48 cycles unmonitored)
March 30, 2004 NASA Goddard Space Flight Center
Thermal Testing Results SummaryAssembly
SetΔ insertion loss during
testing
Overall Change in loss post testing, 90
cycles
Max insertion loss during
testing
Visual Inspection post test side A
Visual Inspection post test side B
MP1 0.09 dB -0.044 dBpower increase
0.058 dB
MP2 0.07 dB -0.015 dB power increase
0.037 dB
MP3 0.04 dB -0.035 dB power increase
0.024 dB
March 30, 2004 NASA Goddard Space Flight Center
Radiation Test Parameters
Tested up to 30 krads in Cobalt 60 chamber:• 10 m of FON1173 (200 micron core fiber) • 10 m of FON1174 (300 micron core fiber)• High dose rate 22.7 rads/min• Low dose rate 11.2 rads/min• While maintaining at temperature of -20°C.• Monitored optical power at 850 nm @ < 1 micro watt of power.
March 30, 2004 NASA Goddard Space Flight Center
Radiation Results for High Dose Test
0 0.5 1 1.5 2 2.5 3 3.5
x 104
0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9High Dose Rate Rad-Induced Attenuation for 200 (red) & 300 (blue) Flexlite Cable
Ra
dia
tio
n I
nd
uc
ed
Att
en
ua
tio
n (
dB
)
Total Dose (rads)
300 micron
0.818 dB
0.892 dB
200 micron
Induced attenuation for both 200 (red), and 300 (blue) micron cable up to 30 krads
22.7 rads/min10 meters of cable
March 30, 2004 NASA Goddard Space Flight Center
Radiation Results for Low Dose Test
0 0.5 1 1.5 2 2.5 3 3.5
x 104
0
0.2
0.4
0.6
0.8
1
1.2
1.4Low Dose Rate Rad-Induced Attenuation for 200 (red) & 300 (blue) Flexlite Cable
Ra
dia
tio
n I
nd
uc
ed
Att
en
ua
tio
n (
dB
)
Total Dose (rads)
300 micron
200 micron
1.024 dB
0.917 dB
Induced attenuation for both 200 (red), and 300 (blue) micron cable up to 30 krads
11.2 rads/min10 meters of cable
Small “glitch” at ~ 20 krads due to fire alarm closing chamber shutter
March 30, 2004 NASA Goddard Space Flight Center
Radiation Results SummaryPart # Type OF
(microns)
Dose rate Atten. @ 30 krads
Ave. temp during testing
Expected atten. 26.1 inches @ 30 krads
FON1173 200 11.2 rads/min 1.024 dB -24.1°C 0.068 dB
FON1174 300 11.2 rads/min 0.917dB -24.1°C 0.061 dB
FON1173 200 22.7 rads/min 0.892 dB -18.3°C 0.059 dB
FON1174 300 22.7 rads/min 0.818 dB -18.3°C 0.054 dB
• Results for 200 and 300 micron fiber are ~ identical.• Results for high and low dose rate tests for both fibers also ~ identical.• Extrapolation model can not be used without further experimentation.• Dose rate differences are attributed with difference in thermal environment.
March 30, 2004 NASA Goddard Space Flight Center
Conclusions• In general, Flexlite and AVIMs assemblies performed with superiority in
comparison to other studies conducted in the past (nepp.nasa.gov/photonics for more information).
• Vibration and Thermal Conclusions: Final change in insertion loss after both vibration and thermal testing is as follows:- MP1, -.04 dB, resulting power increase
- MP2, -.02 dB, resulting power increase
- MP3, -.04 dB, resulting power increase
• Radiation Conclusions: - Since extrapolation method can not be used best assumption is by usage
of lower dose rate results. Actual MLA dose rate will be .011 rads/min.- Using 11.2 rads/min results, expected losses will be less than .07 dB for
each 26.1 inch assembly at –20ºC at a total dose of 30 krads under “dark conditions” or without power enough to provide photobleaching annealing effects.
- Both FON1174 and FON1173 perform identical.
Post all environmental testing: MP1, 0.03 dB; MP2, 0.05 dB; MP3, 0.03 dB
March 30, 2004 NASA Goddard Space Flight Center
AcknowledgementsSpecial thanks to NASA Electronic Parts and Packaging Program &
MESSENGER, Mercury Laser Altimeter Program for funding of this work.Additional thanks to
Dr. Henning Leidecker (always!)Darryl Lakins
Dr. Charles BarnesPhillip Zulueta
Luis A Ramos-Izquierdo Arlin Bartels
For resources and program management support
For more information see the websites:http://nepp.nasa.gov/photonicshttp://misspiggy.gsfc.nasa.gov/photonics
Special thanks to the WebEx team for making this possibleJeannette Plante & Carl Szabo