2006-2007 - Kennedy Space Center Technology Transfer Office

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Aerocoat 7 Replacement CoatingsKennedy Space Center has used Aerocoat 7 (AR-7) to protect stainless-steel flex hoses atCorrosion Launch Complex (LC-39) and hydraulic lines of the Mobile Launcher Platform (MLP)Controlbecause it provides excellent corrosion protection in low-temperature applications. TheSovereign Company produced AR-7 exclusively for NASA but discontinued productionbecause the coating released high levels of volatile organic compounds (VOCs) and had a significantenvironmental impact. The purpose of this project was to select and evaluate potential replacementcoatings for AR-7 that would be more environmentally sound.The physical and mechanical properties of commercially available coatings were investigated throughthe Internet. The ideal coating would be fluid enough to penetrate the outer mesh of a stainless-steelflex hose and coat the inner hose, and flexible enough to withstand the movement of the hose, as wellas the expansion and contraction of its metal caused by changes in temperature. It would also be easyto apply and prepare samples for testing. Ideally, only a single coat would be necessary, applied bybrushing, spraying, or dipping.Forty-one coatings were initially selected. After evaluating the candidates against informationobtained from the Internet and coating manufacturers, we narrowed the list to 15 coatings. After thecoatings were applied, six were removed from consideration because of their reactivity, short pot life,or long curing time.Accelerated corrosion tests were performed in the salt fog chamber of the NASA CorrosionTechnology Laboratory, according to the guidelines of ASTM B117. After 500 hours of exposure,five coatings performed as well as or better than AR-7 and two others were eliminated from thestudy. Figure 1 shows coatings that performed worse than AR-7, the same as AR-7 (AR-7 was thecontrol), and better than AR-7. Sample (a) was one of the coatings eliminated from the study.After 1,000 hours in the chamber, even the best-performing coatings had blisters or creepage alongthe scribe. Only two of the unscribed coatings had no blisters or corrosion spots. The four bestperformers were selected for long-term exposure testing, and scribed samples of these coatings areshown in Figure 2. After 1,500 hours of exposure, none of the coatings performed as well as thecontrol.This study will continue through FY 2008 with further atmospheric exposure and cryogenic testing.Before being included in the list of qualified products in NASA-STD-5008, the replacement forAR-7 must demonstrate that it provides acceptable corrosion protection after exposure for 18 monthsat the NASA Corrosion Technology Laboratory beachside atmospheric-exposure test site.Contact: Dr. Luz Marina Calle , NASA-KSC, (321) 867-3278Participating Organizations: NASA-KSC (Janice K. Lomness) and ASRC Aerospace (Rubiela D. Vinje andJerome P. Curran)12 Spaceport Structures and Materials
Figure 1. After 500 hours of salt fog exposure, coatings performed (a) worsethan AR-7 (the control coating) and (c) better than AR-7.Figure 2. After 1,000 hours of salt fog exposure, all of the coatings showed degradation.KSC Technology Development and Application 2006-200713
Page 5 and 6: ForewordSuccessful technology devel
Page 7 and 8: ContentsSpaceport Structures and Ma
Page 9 and 10: Contents (continued)Process and Hum
Page 11 and 12: IntroductionJohn F. Kennedy Space C
Page 13 and 14: Constellation SystemsSurfaceSystems
Page 15 and 16: Spaceport Structures and MaterialsK
Page 17 and 18: 20181614∆ E1210Modified Sensor Be
Page 19 and 20: Initial results of the EDEM model o
Page 21 and 22: Contacts: Dr. Carlos I. Calle ,NASA
Page 23 and 24: Close examination of the corrosions
Page 25: Adhesion at Failure (psi)2500200015
Page 29 and 30: Contacts: Dr. Paul E. Hintze , NASA
Page 31 and 32: Figure 2. Repairs to various types
Page 33 and 34: on top of the cuvette contains the
Page 35 and 36: Figure 2. A corrugated NiTi sheet e
Page 37 and 38: The PLTD can be used to (1) calibra
Page 39 and 40: 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 and 92:
140000120000100000Signal80000600004
Page 93 and 94:
Contacts: Dr. Barry J. Meneghelli ,
Page 95 and 96:
60555045Comparative k-value (mW/m-K
Page 97 and 98:
a compatible spacecraft model where
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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
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Appendix AKSC High-Priority Technol
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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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