2006-2007 - Kennedy Space Center Technology Transfer Office

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Wireless Inclinometer Calibration SystemA special system was fabricated to properly calibrate the wireless inclinometer, a newDigital-Communication device that will measure the Orbiter’s hang angle. The wireless inclinometer has aTechnology Upgradesunique design and method of attachment to the Orbiter that will improve the accuracyof the measurements, as well as the safety and ease of the operation. The systemproperly calibrates the four attached inclinometers, in both the horizontal and vertical axes, withoutneeding to remove any of the component parts.The Wireless Inclinometer Calibration System combines (1) a calibration fixture that emulates thepoint of attachment to the Orbiter in both the horizontal and vertical axes and the measurementsurfaces, (2) an application-specific software program that accepts calibration data such as dates, zerofunctions, or offsets and tables, and (3) a wireless interface module that enables the wireless inclinometerto communicate with a calibration PC.The stainless-steel mounting fixture emulates a mount to the Orbiter ground support equipment(GSE) door frame on the aft fuselage compartment. This design accounts for the 8-degree offset fromthe fuselage parallel to the Orbiter when the inclinometer is mounted in the horizontal position. Theoutside walls of the fixture can accommodate mounting to the Calibration Laboratory measurementtilt table in the proper axes, and the open-box design is self-supporting both in the upright position(equivalent to Orbiter horizontal) and when rotated 90 degrees (Orbiter in the vertical position). Themounting location side of the fixture is designed to ensure that the inner walls and the outer wallsare parallel. The opposite wall of the fixture is characterized to account for the 8-degree (plus/minusthe fabrication offset) difference between the mounting edge and the centerline of the Orbiter to themounting wall. The wall adjacent to the mounting wall is characterized as 90 degrees (plus/minus thefabrication offset) off the mounting wall. The wall opposite the mounting wall has the outside surfaceas flat as possible. Since it is impossible to fabricate a perfect fixture, the device lends itself to characterizationof known values.The software application consists of a LabVIEW runtime program with a user-friendly interface fora desktop or laptop in a Windows XP environment. The operator can download previous calibrationdata and upload new calibration dates, special notes, and offsets. Both old and new data can be savedin text format for use in spreadsheets. In addition, the software attempts to find coefficients that willconvert the readings from the sensor into values that will match the real angle values. The operatorcan choose the number of coefficients to be used.The wireless interface module is powered directly from thePC or desktop USB port. Wireless communication permitsthe entire remote wireless inclinometer to be calibrated as aunit.aThough the wireless inclinometer calibration systemwas designed exclusively to support Orbiter processingoperations, the system requires only minor hardware andsoftware modifications to be ready for aircraft, military,industrial and construction applications. The benefits aremuch simpler calibration procedures, more reliable measurements,and lower maintenance costs.Calibration fixture.114 Command, Control, and Monitoring Technologies
Contact: Paul J. Mackey , NASA-KSC, (321) 867-6682Participating Organization: ASRC Aerospace (Norman N. Blalock, Bradley M. Burns, and Carlos E. Zavala)Mounting location and critical dimensions.Calibration system interface module.Wireless inclinometer concept.Application software.KSC Technology Development and Application 2006-2007115
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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)
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Hail Size Distribution MappingA 3-D
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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
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
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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 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 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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