2006-2007 - Kennedy Space Center Technology Transfer Office

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Cryogenic Moisture Analysis of Spray-On Foam Insulation (SOFI)Thermal ProtectionSystem (TPS)EnhancementsThe NASA Cryogenics Test Laboratory at Kennedy Space Center conducted long-termtesting of SOFI materials under actual-use cryogenic conditions. The lab tested NCFI24-124 (acreage foam), BX-265 (close-out foam, including intertank flange and bipodareas), and a potential alternate material, NCFI 27-68 (acreage foam with the flameretardant removed).Specimens of all three materials were placed at a site that simulated aging (the Vehicle Assembly Building[VAB]) and a site that simulated weathering (Atmospheric Exposure Test Site [beach site]). After aging/weathering intervals of 3, 6, and 12 months, the samples were retrieved and tested for their ability to absorbmoisture under conditions similar to those experienced by the Space Shuttle External Tank (ET) during theloading of cryogenic propellants.The Cryogenic Moisture Apparatus (CMA) is designed to determine the amount of water or ice takeninto the specimen under actual-use cryogenic conditions. To simulate actual-use conditions, the top of thespecimen is fixed at the temperature at which nitrogen remains liquid, while the bottom (outside) face isexposed to moist air at a constant humidity (90 percent) inside an environmental chamber. In order tothe keep the air quiet and the convection currents minimized, fans are not used. The surface temperaturesof the specimen are also monitored by thermocouples and recorded by a LabVIEW data acquisitionsystem. The edges of the CMA are guarded from moisture intrusion and from substantial heat leakage.The moisture uptake is measured by the water or ice taken into the specimen vertically (i.e., through thethickness of the specimen). Figure 1 shows the CMA and test setup.All tests were conducted at ambient pressure (760 torr). The typical run time was 8 hours from start ofcooldown to simulate the timeline for loading the Space Shuttle ET with cryogenic propellants. The warmboundary temperature (WBT) was approximately 293 K and the cold boundary temperature (CBT) wasapproximately 78 K. The specimen, including its edge guard ring, was quickly removed and replaced everyhour to measure the weight gain.Some results for the weathering case are shown in the table. These typical results are averaged values fora number of test runs and are given in percentage weight gains, using a 7-inch effective heat transfer area(between the 6-inch-diameter cold chamber and the 7-inch-diameter exposed face) for an 8-hour cold soak.Figures 2 and 3 compare the weight change for specimens of NCFI 24-124 at the aging (VAB) and at theweathering (beach) sites.Figure 1. Cryogenic Moisture Apparatus: schematic (left) and overall view, including environmental controlchamber (right).78 Fluid System Technologies
Contacts: Dr. Barry J. Meneghelli , ASRC Aerospace, (321) 867-4011; andJames E. Fesmire , NASA-KSC,(321) 867-7557Participating Organization: ASRC Aerospace (Walter H. Hatfieldand Kenneth W. Heckle, Sr.)Weight gain results of SOFI weathering tests.MaterialBaseline(%)3 Month(%)6 Month(%)NCFI 24-124 30 78 74NCFI 27-68 32 72 72BX-265 30 70 95Specimen Weight Change (%)10090807060504030M102 NCFI 24-124 A0 R2M103 NCFI 24-124 A0 R1M124 NCFI 24-124 A0.59 (Test Stand, Front) R1M124 NCFI 24-124 A0.59 (Test Stand, Front) R2M105 NCFI 24-124 A3 (Test Stand, Front) R1M107 NCFI 24-124 A3 (Test Stand, Back) R1M107 NCFI 24-124 A3 (Test Stand, Back) R2M117 NCFI 24-124 A6 (Test Stand, Front) R1M117 NCFI 24-124 A6 (Test Stand, Front) R2M112 NCFI 24-124 A6 (Test Stand, Back) R1M112 NCFI 24-124 A6 (Test Stand, Back) R2M133 NCFI 24-124 A12 (Test Stand, Front) R1M133 NCFI 24-124 A12 (Test Stand, Front) R2M134 NCFI 24-124 A12 (Test Stand, Back) R1M134 NCFI 24-124 A12 (Test Stand, Back) R2201000 1 2 3 4 5 6 7 8 9Cold Soak Time (hours)Figures 2. Uptake of cryogenic moisture in aged NCFI 24-124 samples(12-month data).Specimen Weight Change (%)10090807060504030M102 NCFI 24-124 A0 R2M103 NCFI 24-124 A0 R1M113 NCFI 24-124 W0.25 R1M113 NCFI 24-124 W0.25 R2M113 NCFI 24-124 W0.5 R3M106 NCFI 24-124 W3 R1M106 NCFI 24-124 W3 R2M106 NCFI 24-124 W3 R3 (machined flat, no rind)M106 NCFI 24-124 W3 R4 (machined flat, no rind)M106 NCFI 24-124 W3 R5 (machined flat, no rind)M115 NCFI 24-124 W6 R1M115 NCFI 24-124 W6 R3M135 NCFI 24-124 W12 R1M135 NCFI 24-124 W12 R2201000 1 2 3 4 5 6 7 8 9Cold Soak Time (hours)Figures 3. Uptake of cryogenic moisture in weathered NCFI 24-124 samples(12-month data).KSC Technology Development and Application 2006-200779
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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)
Page 41 and 42: 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: 140000120000100000Signal80000600004
Page 95 and 96: 60555045Comparative k-value (mW/m-K
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
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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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