2006-2007 - Kennedy Space Center Technology Transfer Office

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Using Indium Tin Oxide To Mitigate Dust on Viewing Ports2007 Center Director’s Discretionary Fund ProjectNASA plans to use a number of onboard viewing ports to measure lunar regolith in situContamination and to monitor robotic and human activities on the lunar or Martian surface. BecauseControlof the size and abundance of dust particles on these bodies, the potential for dust toocclude viewing ports and windows is high enough to threaten system lifetime andreliability, especially when activities rely on relaying video to either a habitat module or controllers onEarth.This project uses a technology being developed by KSC’s Electrostatics and Surface Physics Laboratoryto remove dust from windowlike surfaces. The technology applies an alternating electric potential tointerlaced electrodes. In this application, we use indium tin oxide (ITO) to create various electrodepatterns in order to determine the most reliable pattern for dust removal. This technology hasapplication to systems where optical clarity is important. Specifically, this project considers the in situresource utilization (ISRU) application of a viewing port for Raman spectroscopy, where the electrodepattern on glass would be coated with a scratch-resistant sapphire film (Al 2O 3).Electrode patterns were tested in ambient and dry air. These patterns included a single-phase square,single-phase circle, single-phase comb, three-phase square, three-phase circle, and three-phase comb.The voltage, frequency, and waveform applied to each screen were varied in search of the best way toremove dust.Of the patterns tested, the three-phase circular spiral was the most efficient at removing dust. Thecircular pattern minimizes the number of abrupt endings to the electrodes, thereby minimizing thepoints where high electric fields could lead to breakdown and sparking. The screen was tested withJSC-1 lunar simulant particles of less than 25 µm in diameter. A majority of the dust was removedwithin 10 s under ambient conditions and within 5 min under dry-air conditions (near 0 percentrelative humidity).We continued screen testing under vacuum conditions to demonstrate proof of concept in a morerelevant environment. Test parameters were varied in a manner similar to the tests performed underambient and dry-air conditions on a glass screen with a spiral ITO pattern coated with a thin film ofsapphire. The clearing of the dust was similar to the clearing demonstrated under dry-air conditions.An additional test successfully demonstrated the use of the screen on and near metal surfaces. Theproximity of the metal surface did not appear to affect how well the screen removed dust. Applicationsfor using the technology on metals range from dust transport mechanisms to clearing dust from sealsand mechanical joints.Key accomplishments were• developing a technique to apply electrode patterns to ITO-coated glass slides up to 0.7 mm thick,• developing a processing technique to remove the uncoated ITO from the glass slides and coat theslides with an insulating material to prevent sparking, and• optimizing test parameters (voltage, waveform, frequency).Key milestones were• determining an efficient pattern for dust removal,• demonstrating the capability of ITO screens to remove dust under high-vacuum conditions, and• demonstrating the capability of ITO screens to remove dust when backed with grounded andungrounded metal plates.Spaceport Structures and Materials
Contacts: Dr. Carlos I. Calle ,NASA-KSC, (321) 867-3274; and Dr. Jacqueline W. Quinn, NASA-KSC,(321) 867-8410Participating Organizations: ASRC Aerospace(Dr. Charles R. Buhler, Judith L. McFall, andMindy L. Ritz) and Appalachian State University(Dr. Sid Clements)Screen pattern design.A 2.3-cm circular spiral on ITO-coated glass at T = 0 s under dry/ambientconditions.A 2.3-cm circular spiral on ITO-coated glass at T = 8 s under dry/ambientconditions.KSC Technology Development and Application 2006-2007
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: Initial results of the EDEM model o
Page 23 and 24: Close examination of the corrosions
Page 25 and 26: Adhesion at Failure (psi)2500200015
Page 27 and 28: Figure 1. After 500 hours of salt f
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
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Autonomous Flight Safety System - P
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The Photogrammetry CubeSpaceport/Ra
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Bird Vision SystemThe Bird Vision s
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Automating Range Surveillance Throu
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Next-Generation Telemetry Workstati
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GPS Metric Tracking UnitAs Global P
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Space-Based RangeSpace-Based Range
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Fluid System TechnologiesKSC Techno
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0.900.850.80Discharge Coefficient,
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Composite seals for performance eva
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140000120000100000Signal80000600004
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Contacts: Dr. Barry J. Meneghelli ,
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60555045Comparative k-value (mW/m-K
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a compatible spacecraft model where
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In an ongoing effort for improvemen
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Low-gravity probe prototype test.th
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Countermeasure for Radiation Protec
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Focused Metabolite Profiling for Di
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Process and Human FactorsEngineerin
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DON uses game technology to enable
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Type of mobile crane that impacted
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SALT proof-of-concept communication
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SSLM CAD model.Our design offers th
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Variables that can be integrated by
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Exploration Supply Chain Simulation
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Nanosensors for Evaluating Hazardou
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Sixty-four-Channel Inline Cable Tes
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Wireless Inclinometer Calibration S
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Generating Safety-Critical PLC Code
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Spacecraft Electrostatic Radiation
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Ion Beam Propulsion StudySpacecraft
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RT-MATRIX: Measuring Total Organic
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Appendix AKSC High-Priority Technol
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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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