2006-2007 - Kennedy Space Center Technology Transfer Office

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GPS Metric Tracking UnitAs Global Positioning Satellite (GPS) applications become more prevalent for land- andGlobal PositioningSystem (GPS) air-based vehicles, GPS applications for space vehicles will also increase. The AppliedMetric Tracking Technology Directorate of Kennedy Space Center (KSC) has developed a lightweight,low-cost GPS Metric Tracking Unit (GMTU), the first of two steps in developing alightweight, low-cost Space-Based Tracking and Command Subsystem (STACS) designed to meetRange Safety’s link margin and latency requirements for vehicle command and telemetry data. Thegoals of STACS are to improve Range Safety operations and expand tracking capabilities for spacevehicles. STACS will track the vehicle, receive commands, and send telemetry data through thespace-based asset, which will dramatically reduce dependence on ground-based assets. The otherstep was the Low-Cost Tracking and Data Relay Satellite System (TDRSS) Transceiver (LCT2),developed by the Wallops Flight Facility (WFF), which allows the vehicle to communicate with ageosynchronous relay satellite. Although the GMTU and LCT2 were independently implementedand tested, the design collaboration of KSC and WFF engineers allowed GMTU and LCT2 to beintegrated into one enclosure, leading to the final STACS.In operation, GMTU needs only a radio frequency (RF) input from a GPS antenna and outputsposition and velocity data to the vehicle through a serial or pulse code modulation (PCM) interface.GMTU includes one commercial GPS receiver board and a custom board, the Command andTelemetry Processor (CTP) developed by KSC. The CTP design is based on a field-programmablegate array (FPGA) with embedded processors to support GPS functions. The programmability ofthe CTP allows designs to be changed and functions to be added without the need to modify thehardware. GMTU is well suited for applications requiring highly reliable metric tracking, such asrobotics, autonomous air and ground vehicles, and manned vehicles. GMTU offers two commandreceivechannels, one output telemetry channel, and Ethernet, serial, and RS-422 interfaces. The unitis conduction-cooled, weighs less than 2 lb, and measures 1.5 by 5.0 by 4.0 inches.GMTU has passed functional, vibration, and electromagnetic interference testing and is scheduledfor flight testing in 2008 aboard a suborbital sounding rocket flight to be launched from WFF. Themain objective of the test is to demonstrate the reliability of GMTU to track the rocket and theoperational reliability of the hardware.The final step in developing STACS will be to integrate and test the hardware and functionalcomponents of GMTU and LCT2.Contacts: Emilio Valencia , NASA-KSC, (321) 861-9074; Christopher S. Forney, NASA-KSC, (321) 867-6825; Robert L. Morrison , NASA-KSC, (321) 867-6687; and Richard B. Birr , NASA-KSC,(312) 867-6301Participating Organizations: NASA-KSC (Brian C. Cheshire) and ASRC Aerospace (Temel Erdogen,William D. Haskell, Michael A. Bertucci, Carlos E. Zavala, and Theresa G. Overcash)66 Range Technologies
GPS Metric Tracking Unit (GMTU).Command and Telemetry Processor (CTP) board developed at KSC.KSC Technology Development and Application 2006-200767
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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
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 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 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
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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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