2006-2007 - Kennedy Space Center Technology Transfer Office

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Thermal Performance of Aged and Weathered Spray-On Foam Insulation(SOFI) Materials Under Cryogenic Vacuum Conditions (Cryostat-4)The NASA Cryogenics Test Laboratory at Kennedy Space Center conducted long-termThermal ProtectionSystem (TPS) testing of SOFI materials under actual-use cryogenic conditions with Cryostat-4. TheEnhancements materials included in the testing were NCFI 24-124 (acreage foam), BX-265 (close-outfoam, including intertank flange and bipod areas), and a potential alternate material,NCFI 27-68, (acreage foam with the flame retardant removed). Specimens of these materials wereplaced at two locations: a site that simulated aging (the Vehicle Assembly Building [VAB]) and a sitethat simulated weathering (the Atmospheric Exposure Test Site [beach site]). After aging/weatheringintervals of 3, 6, and 12 months, the samples were retrieved and tested for their thermal performanceunder cryogenic vacuum conditions with test apparatus Cryostat-4.Cryostat-4 is a liquid-nitrogen boiloff calorimeter designed to determine the apparent thermalconductivity (k-value) of thermal insulation systems under actual-use cryogenic vacuum conditions.The method is comparative in that the total heat load to the test chamber includes a minor butrepeatable parasitic heat leakage rate. The residual gas supplied to the vacuum chamber is nitrogen.The boiloff flow from the test chamber is in direct proportion to the total heat transfer rate throughthe thickness of the test article. Flow rate is typically averaged over the liquid level from 4 to0 percent (near empty) to calculate the comparative k-value.The SOFI test articles were 203 mm in diameter, with a nominal thickness of 25.4 mm. Tests wereconducted starting at ambient pressure (760 torr) and working down, decade by decade of vacuumpressureincrements, to high vacuum (below 1×10 –3 torr). At least eight cold vacuum pressure testswere performed for each test series. The warm boundary temperature (WBT) was approximately293 K and the cold boundary temperature (CBT) was approximately 78 K. Figure 1 shows theinstallation of a SOFI test article.The foams were tested in the baseline, aged, and weathered conditions. Here baseline means that thespecimens were not weathered and only slightly aged. Specimens with rind were necessarily sandeddown to a flat surface finish for good thermal contact with the warm and cold sides of the cryostat.Surface Temperature MeasurementSensorLocationT1, T3 Cold Boundary Temperature (CBT)T2T4, T5VC1, VC2, VC3VC4, VC5, VC6Top of Cold MassWarm Boundary Temperature (WBT)Vacuum Chamber ExteriorHeater TemperatureFigure 1. The SOFI test specimen is installed between the cold mass tank and the warm boundary of insulation inCryostat-4.80 Fluid System Technologies
60555045Comparative k-value (mW/m-K)40353025201510F156s NCFI 24-124 A0 40F160s NCFI 24-124 A3 40F175s NCFI 24-124 A6 39F187s NCFI 24-124 A12 39F161s NCFI 24-124 W3 40F168s NCFI 24-124 W6 34F182s NCFI 24-124 W12 39F158s BX-265 A0 37F165s BX-265 A3 35F171s BX-265 A6 35F176s BX-265 A12 36F163s BX-265 W3 36F170s BX-265 W6 32F180s BX-265 W12 36F164s NCFI 27-68 A0 39F166s NCFI 27-68 A3 38F172s NCFI 27-68 A6 38F181s NCFI 27-68 A12 38F167s NCFI 27-68 W3 39F173s NCFI 27-68 W6 40F185s NCFI 27-68 W12 370.1 1 10 100 1,000 10,000 100,000 1,000,000Cold Vacuum Pressure (millitorr)Figure 2. The variation of comparative k-value with cold vacuum pressure forall Cryostat-4 SOFI test specimens. The boundary temperatures are 293 Kand 78 K. The residual gas is nitrogen.Figure 2 shows the results for the cryogenic thermal-performance testing of the aged andweathered SOFI materials. The apparent thermal conductivity (k-value) is reported in thestandard SI units (milliwatts per meter Kelvin), but these numbers are comparative and mayonly be applied among the test specimens listed in this report.Contacts: Dr. Barry J. Meneghelli , ASRC Aerospace, (321) 867-4011; andJames E. Fesmire , NASA-KSC, (321) 867-7557Participating Organization: ASRC Aerospace (Walter H. Hatfield and Kenneth W. Heckle, Sr.)KSC Technology Development and Application 2006-200781
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ForewordSuccessful technology devel
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ContentsSpaceport Structures and Ma
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Contents (continued)Process and Hum
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IntroductionJohn F. Kennedy Space C
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Constellation SystemsSurfaceSystems
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Spaceport Structures and MaterialsK
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20181614∆ E1210Modified Sensor Be
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Initial results of the EDEM model o
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Contacts: Dr. Carlos I. Calle ,NASA
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Close examination of the corrosions
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Adhesion at Failure (psi)2500200015
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Figure 1. After 500 hours of salt f
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Contacts: Dr. Paul E. Hintze , NASA
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Figure 2. Repairs to various types
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on top of the cuvette contains the
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Figure 2. A corrugated NiTi sheet e
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The PLTD can be used to (1) calibra
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SEM images of neat MWNT fibers: (a)
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Contacts: Trent M. Smith
Page 43 and 44: Figure 1. An isometric cutaway view
Page 45 and 46: Figure 2. Quartz sand flowing in th
Page 47 and 48: Figure 2. Top images show how the e
Page 49 and 50: Sand volume fraction contour at t =
Page 51 and 52: Integrated LWRD/RVC engineering bre
Page 53 and 54: Mean relative percentage change in
Page 55 and 56: We compared the model’s predictio
Page 57 and 58: Figure 2. Three-dimensional simulat
Page 59 and 60: Figure 3. Camera calibration model.
Page 61 and 62: The sketch in Figure 2 shows alaunc
Page 63: Figure 2. Signal generator (right)
Page 66 and 67: Hail Size Distribution MappingA 3-D
Page 68 and 69: Launch Pad 39 Hail Monitor Array Sy
Page 70 and 71: Autonomous Flight Safety System - P
Page 72 and 73: The Photogrammetry CubeSpaceport/Ra
Page 74 and 75: Bird Vision SystemThe Bird Vision s
Page 76 and 77: Automating Range Surveillance Throu
Page 78 and 79: Next-Generation Telemetry Workstati
Page 80 and 81: GPS Metric Tracking UnitAs Global P
Page 82 and 83: Space-Based RangeSpace-Based Range
Page 85 and 86: Fluid System TechnologiesKSC Techno
Page 87 and 88: 0.900.850.80Discharge Coefficient,
Page 89 and 90: Composite seals for performance eva
Page 91 and 92: 140000120000100000Signal80000600004
Page 93: Contacts: Dr. Barry J. Meneghelli ,
Page 97 and 98: a compatible spacecraft model where
Page 99 and 100: In an ongoing effort for improvemen
Page 101: Low-gravity probe prototype test.th
Page 104 and 105: Countermeasure for Radiation Protec
Page 106 and 107: Focused Metabolite Profiling for Di
Page 109 and 110: Process and Human FactorsEngineerin
Page 111 and 112: DON uses game technology to enable
Page 113 and 114: Type of mobile crane that impacted
Page 115 and 116: SALT proof-of-concept communication
Page 117 and 118: SSLM CAD model.Our design offers th
Page 119 and 120: Variables that can be integrated by
Page 121: Exploration Supply Chain Simulation
Page 124 and 125: Nanosensors for Evaluating Hazardou
Page 126 and 127: Sixty-four-Channel Inline Cable Tes
Page 128 and 129: Wireless Inclinometer Calibration S
Page 130 and 131: Generating Safety-Critical PLC Code
Page 132 and 133: Spacecraft Electrostatic Radiation
Page 134 and 135: Ion Beam Propulsion StudySpacecraft
Page 136 and 137: RT-MATRIX: Measuring Total Organic
Page 139 and 140: Appendix AKSC High-Priority Technol
Page 141 and 142: Risk Assessment ToolMission Data Fe
Page 143 and 144: Appendix BInnovative Partnership Pr
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system for the Government, using th
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tracking objects after launch, and
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2006-2007 - Kennedy Space Center Technology Transfer Office

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