2006-2007 - Kennedy Space Center Technology Transfer Office

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Solid-State Lighting Module (SSLM)Energy-EfficientLighting SystemThe project’s goal was to build a light-emitting-diode (LED)-based light fixture thatis identical in fit, form, and function to the existing International Space Station (ISS)General Luminaire Assembly (GLA) light fixture and fly it on the ISS in early FY 2008as a Station Detailed Test Objective (SDTO).Comparison of GLA and SSLMSpecification GLA SSLM SSLM Benefits to ISS/Future SpacecraftPower 30 W 30 W n/aPhoto-optic Luminous Flux 449 lm 479 lm Better illumination = safer operationMass 4.0 kg 3.6 kg Less up-mass = more flexibility for manifestingInput Voltage 120 VDC 120 VDC n/aDimmability flickering 0–100% No flicker = less eye strainPlanned Life ~5,000 hr ~50,000 hr Less maintenance = less up-mass and crew timeSSLM.102 Process and Human Factors Engineering Technologies
SSLM CAD model.Our design offers the following strengths:• proven component hardware: Our design uses components flown in other KSC-developedhardware;• “heat path” thermal pad: LED array heat is transferred from the circuit board by silicon pad,negating the need for a cooling fan;• variable colorimetry: The output light color can be changed by inserting different LEDcombinations.Contact: Daniel C. Shultz , NASA-KSC, (321) 861-2896Participating Organization: Bionetics Corporation (Trevor Murdoch, April C. Spinale, and Howard W. Wells)KSC Technology Development and Application 2006-2007103
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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
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Figure 1. An isometric cutaway view
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Figure 2. Quartz sand flowing in th
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Figure 2. Top images show how the e
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Sand volume fraction contour at t =
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Integrated LWRD/RVC engineering bre
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Mean relative percentage change in
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We compared the model’s predictio
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Figure 2. Three-dimensional simulat
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Figure 3. Camera calibration model.
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The sketch in Figure 2 shows alaunc
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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
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: SALT proof-of-concept communication
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
Page 145 and 146: system for the Government, using th
Page 147: tracking objects after launch, and
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2006-2007 - Kennedy Space Center Technology Transfer Office

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