2006-2007 - Kennedy Space Center Technology Transfer Office

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Space-Based RangeSpace-Based Range (SBR), previously known as Space-Based Telemetry and Range SafetyGlobal PositioningSystem (GPS) (STARS), is a multicenter NASA proof-of-concept project to determine if space-basedMetric Tracking communications using NASA’s Tracking and Data Relay Satellite System (TDRSS) cansupport the Range Safety functions of acquiring tracking data and generating flighttermination signals, while also providing broadband Range User data such as voice, video, andvehicle/payload data.Figure 1. Sounding rocket launch.There was a successful test of the Range Safety system at Wallops Flight Facility (WFF) onDecember 20, 2005, on a two-stage Terrier-Orion spin-stabilized sounding rocket. SBR transmittedGPS tracking data and maintained links with two TDRSS satellites simultaneously during the10‐min flight. The payload section deployed a parachute, landed in the Atlantic Ocean about90 miles downrange from the launch site, and was successfully recovered.During the Terrier-Orion tests flights, more than 99 percent of all forward commands and more than95 percent of all return frames were successfully received and processed. The time latency necessaryfor a command to travel from WFF over landlines to White Sands Complex and then to the vehiclevia TDRSS, be processed onboard, and then be sent back to WFF was between 1.0 s and 1.1 s.The forward-link margins for TDRS‐10 (TDRS East [TDE]) were 11 dB to 12 dB ±2 dB, and forTDRS‐4 (TDRS Spare [TDS]) were 9 dB to 10 dB ±1.5 dB. The return-link margins for both TDEand TDS were 6 dB to 8 dB ±3 dB.There were 11 flights on an F-15B at Dryden Flight Research Center (DFRC) between November2006 and February 2007. The Range User system tested a 184‐element TDRSS Ku-band (15 GHz)phased-array antenna with data rates of 5 Mbps and 10 Mbps. This data was a combination ofblack-and-white cockpit video, Range Safety tracking and transceiver data, and aircraft and antennacontroller data streams. IP data formatting was used. The Range Safety system used the previouslyflown S-band transceiver to validate the forward and return links. Several “flyaway” maneuvers testedthe transition from launch-head to satellite for the forwardlinks.Figures 1 through 3 show the phased-array antenna mountedon the F-15 and architecture of the sounding rocket.Figure 4 shows the Range User return link margins asfunctions of antenna elevation for 5‐Mbps and 10‐Mbpsflights. Link margins greater than 9 dB could not bemeasured, so it can only be said that the link margins weregreater than 9 dB for elevations above 30°.During the F-15 test flights, custom algorithms used thevehicle position and attitude to steer the phased-arrayantenna toward TDRSS West (TDW) at 174° W longitudewith a pointing error typically much less than 1°. Themeasured data and video latency for the Range User systemwas about 0.4 s. More than 99 percent of the Range Userframes were locked for both 5 Mbps and 10 Mbps when theantenna azimuth performance was within nominal operatingparameters and more than 98 percent when these parameterswere intentionally exceeded. There was a reasonably smoothtransition between the Range Safety launch-head and satellite68 Range Technologies
Figure 2. Sounding rocket.forward links within 10 km to 20 km of the launch-headfor a launch-head power level of –84 dBm. The antennapattern of the four S-band telemetry Range Safetyantennas on the F-15 (two forward and two return, withone set of each on the top and bottom of the F-15) wasmeasured at the Benefield Anechoic Facility at DFRC.Contact: Dr. James C. Simpson ,NASA-KSC, (321) 867-6937Figure 3. Phased-array antenna on the F15.5-Mbps Flight5-Mbps Flight No-lock conditions caused when TDRS passedthrough the antenna zenith and the aircraft dynamics exceededazimuth performance.10-Mbps FlightNo-lock conditions caused when TDRS passed through the antennazenith and signal reacquisition was delayed at the beginning of thetest maneuver.Figure 4. Link margin results for 5- and 10-Mbps flights. Note: No coverage was guaranteed by the manufacturer below30° elevation.KSC Technology Development and Application 2006-200769/70
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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
Page 31 and 32: Figure 2. Repairs to various types
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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 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
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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
Page 130 and 131: 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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