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Thermal Interface Comparisons Under Flight-like Conditions
Juan Rodriguez-Ruiz NASNGoddard Space Flight Center, Mail code 545,
Greenbelt, MD 20771 Juan. E. Rodriguez-RuizQnasa. gov
1 /
NASA's Goddard Space Flight Center LRO Interface Conductance Test [email protected]
https://ntrs.nasa.gov/search.jsp?R=20080031739 2018-06-16T10:43:06+00:00Z
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Agenda
Introduction & Test Goals Test Setup - Materials & specifications - Requirements - Configuration
Original setup lessons learned Thermal Interface Materials Background Results Conclusions & Implementation
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Introduction
Thermal interface materials are used in bolted interfaces to promote good thermal conduction between the two. The mounting surface can include panels, heat pipes, electronics boxes, etc.. . On Lunar Reconnaissance Orbiter (LRO) project the results are directly applicable - Several high power avionics boxes - Several interfaces from RWA to radiator through heat pipe network
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Test Goals
Test interface materials tested were already scheduled to be used on flight or were considered alternatives Meet requirements for the Lunar Reconnaissance Orbiter (LRO) project - 1 W/(in2*K)
Comparison of commonly used thermal interface materials under more practical conditions Test runs according to Lunar Reconnaissance Orbiter Thermal interface material application procedure(45 1 -
LRO Interface Conductance Test &.L NASA'. roddad Space Flight Center 3uan.E.Rodriguez-Ruit@lna~.gov 's.-.h
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Test Runs
Dry joint eGraf HITHERM-1210 (10 mil) NuSil CV-2946 with 5 mil Teflon film ChoSeal -1 285 Indium Grafoil (5 mil) Copper picture frame with NuSil combination NuSil with spray Teflon Arathane (60% Boron Nitride) with spray Teflon
NASAs Goddard Space Flight Center LRO Interface Conductance Test [email protected]
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Tested Surfaces
'qk NASA's Goddard Space Flight Center LRO Interface Conductance Test ,I 2 [email protected] - h
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Materials And Specifications @B Thermocouples: Type T (30 AWG) x 35 Chiller fluid: - 30% Propynol & 70% water Bolts: Socket-head stainless steel (lubricated with Braycote) Torque values taken from LRO Torque Spec - Heat pipe: 10-32 (30 in-lb) - Baseplate: 8-32 (26 in-lb)
Minco heaters using Pressure Sensitive Adhesive (PSA) and aluminum tape over them. Maximum heater density kept under 3 W/in2 - Baseplate: 5" X 5" (1 13.7 f2) - Heat Pipe: 1.5" X 12" (260 0)
Data collection software: Labview 7.1 Setup covered with MLI to prevent heat loss
LRO Interface Conductance Test NASA's Goddard Space Flight Center [email protected]
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I ---?*286 15 AVE
rn 5.992
61 3
NASA's Goddard Space Flight Center LRO Interface Conductance Test [email protected]
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%?- NASA's Goddard Space Flight Center LRO Interface Conductance Test
it \u3 3uan.E.Rodriguez-Ruiz6nasa.gov
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Test Requirements
Pressure - < 1 0-3 Torr (1 Torr = 133.32 Pa) - Controlled by:
Mechanical pump LN2 cooled scavenger plate (@ -1 75°C)
Steady-state temperature stability criteria - (< 0.5 "Clhr)
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Test Configurations
Two sink temperatures: - Cold: -10°C to 0°C - Warm: 25°C to 35°C
Two power levels: - Baseplate
High: 75 W Low: 50 W
- Heat Pipe High: 60 W Low: 40 W
- NASA's boddard Space Flight Center ,dk>sI
LRO Interface Conductance Test [email protected]
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Original Setup Lessons Learned! o i i No use of scavenger plate Software problems No thorough sanity check of TC's Cooling heat exchanger with LN2 - Too powerful (cooling in short bursts)
Chiller not cooling enough (added Propynol to increase temperature range) Taking data every 2 seconds Heater power too low
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Original Setup Lessons Learned!
Original base plate used was spare SDO CDH baseplate in an attempt to capture actual box stiffness -- Uncomfortable and non-uniform heater locations - Not very flat surface
Ti i 9 793 TC lo 1C 11
9.159 U,,6j 13 AK 9'599 9.740 •
10% I 0 183 10.370 T I AYE TC W TC 21
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Interface Materials
LRO Interface Conductance Test NASA's Goddard Space Flight Center [email protected]
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Expanded carbon sheet - Provides good thermal contact under regular pressure - Can be a particulate shedding material - 10 mil thick (0.01 in)
Test setup: - Baseplate: Four 6"X 6" sheets - Heat pipe: Two 3"X 6" sheets
4% NASA's Goddard Space Flight Center ' & I A
LRO Interface Conductance Test [email protected]
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Silicone sheet loaded with silver-plated aluminum particles to provide good thermal and electrical conduction Good thermal contact relies on a squeezing pressure so it does not perform well away from bolts and clamps 20 mil thick Bake out required for better performance (at 175°C in an air oven for 24 hours)
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Indium
99.99% Indium foil No sample shown: - Carcinogenic - Skin irritant
Lustrous silver-white metal Soft, malleable and ductile
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It is a silicone based fluid (may pose a contamination risk) Stored in 5cc syringes at very low temperatures and thawed before application. It conforms to the shape of the interface then it solidifies at room temperature. Test setup: - Teflon film 5 mil (0.005 in) - Strips: -118" wide, I" between strips
NASA's Goddard Space Flight Center &ldf
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Copper Picture Frame With NuSil @a
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5 mil Cu sheet Center: 0.10 W/(in2 *K) 5 mil Cu picture frame (taped up) 1 " separation between strips Perimeter: 0.40 W/(in2*K)
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112 mil Cu sheet Center: 0.10 W/(in2*K1 1 r
6 mil Cu picture frame (cut) 314" separation between strips
Perim.eter: 0.33 W/(in2*K)
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5 mil Teflon film 6 mil Cu picture frame (cut) 314" separation between strips
Center: 0.22 W/(in2 *K)
Perimeter: 0.82 W/(in2*K)
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Results
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Sample Sketch
. . .. . .. ; 3.286
TS AVE
m-11.741 6 1 3
NASA's Goddard Space Flight Center
-- - TC 28. -4 296 -3.106 TC 35 -3 191 TC 30 + -3 264
-13 AVE TC 2 2 e -2.571 TC 23, -2 861
TC21 0 -4.099 6 1 2 -2.717
14 AVE
TC24
-1.012
~ ~ 2 6 1 ) -2.359 TC 25 a -2
TC 27* -3 669
LRO Interface Conductance Test Juan.E.Rodriguez-Ruiz@nasa.~v
2 8
TC 3 2 8 -3 000 ~ c 6 2.306
TC 34 .) -3 890 TC a@ -2.731
TC5 l -3 568
-3.289 -2 904 -2 724 ".
-2.434 .,.-
-2 935
T C 7 e
-3 037
O T C 1
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449
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2. . ,. . \ "
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TlAVE
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-1 456
T2 AVE
TC 13,
3.80 ---
102500
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@ Interface Conduction Calculation
Cil := - T $Area ('surface sin
Units: Wl(in2*K)
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Heat Pipe interface conductance
Dryjoint eGraf NuSil ChoSeal Grafoil Spray teflon nusil spray teflon1Arathane
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Heat Pipe % Variation
- - .-
Dryjoint eGraf NuSil ChoSeal Grafoil Spray teflon nusil Spray teflon1Arathane
- NASA's Goddard Space Flight Center -L- '<.
LRO Interface Conductance Test [email protected]
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Baseplate interface conductance
.-- 1.80 I 7- ------ _- - -111 -- _
& NASA's Goddard Space Flight Center LRO Interface Conductance Test [email protected]
- - - .
' Perimeter
1. Center , - .
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Baseplate % Variation
- - - -- - - -
I - 1 I3 Perimeter ; I
Center I - . I
NA!SAes Goddard Space Flight Center c;
LRO Interface Conductance Test [email protected]
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Conclusions
Superiority of NuSil in areas not bolted down vs. solid sheets Exceptional performance of eGraf around bolted areas and all around in stiffer surfaces On picture frame variation it was found that copper frame did not enhance the perimeter thermal conductance. Performance was best when thin teflon sheet was used instead of copper Undergoing supplemental tests - Nusil with spray teflon - Arathane loaded with 60% Boron Nitride with spray teflon
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Implementation
Avionics on ITP panel - CDH, PSE, STRANS (Copper picture frame with NuSil) - MiniRF receiver and controller, possibly KaTWT (eGraf)
MiniRF receiver & controller
, b, NASA's Goddard Space Flight Center i- -
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LRO Interface Conductance Test [email protected]
STRANS
-KaTWT
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Implementation
Avionics on ITP panel - CDH, PSE, STRANS (Copper picture frame with NuSil) - MiniRF receiver and controller, possibly KaTWT (eGraf)
MiniRF receiver & controller --- !12 NASA's Godclard Space Flight Center LKU inremace Lonauctance I e n [email protected]
STRANS
KaTWT
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Implementation
Heat pipe interfaces - RWA heat pipe joints (eGraf) - Dual bore heat pipes to radiator (eGraf)
1 ] Radiator 9
1 DB Pipes n 4G10 S~acer
ITP Sim
Q I+- @ saidle -
Pipe Sims
Lower 1-1 headers
RWA pipes
, NASA's Goddard Space Flight Center J .<;
Brackets
Baseplates
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Heat Pipe
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LRO Interface Conductance Test 3uan.E.Rodriguez-Ruir6nasa.gov