2006-2007 - Kennedy Space Center Technology Transfer Office

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Autonomous Flight Safety System – Phase IIIThe Autonomous Flight Safety System (AFSS) is a joint KSC and Wallops FlightDecision/DataModels and Facility project that uses tracking and attitude data from onboard Global PositioningAnalysis System (GPS) and inertial measurement unit (IMU) sensors and configurable rule-basedalgorithms to make flight termination decisions. AFSS objectives are to increase launchcapabilities by permitting launches from locations without range safety infrastructure, reduce costs byeliminating some downrange tracking and communication assets, and reduce the reaction time forflight termination decisions.The AFSS flew on a Terrier Improved-Orion two-stage sounding rocket at White Sands MissileRange on April 5, 2006. Two GPS sensors and two independently programmed processors were used,each with a different set of mission rules. The mission rules set for one processor were configured sothat a nominal flight would not result in any flight termination actions. The mission for the otherprocessor included three additional rules so that multiple destruct activations would occur duringa nominal flight. Because the AFSS was not connected to a flight termination system, it could notinitiate any destruct actions.Preflight loading and verification went smoothly. However, the Ashtec G12 GPS receiver lost lockon liftoff and did not regain it until after the flight was over. The Javad GPS receiver maintainedlock throughout the flight. The rocket behaved nominally, the nominal processor did not executeany unplanned destruct actions, and the errant processor successfully initiated three destructactions as planned. Both processors provided navigation and status messages to observers via thevehicle telemetry stream. These messages were also stored in the nominal processor’s nonvolatile(flash) memory for the entire operation. The errant processor’s flash memory chip became partiallydislodged during the flight and stopped recording at T+335 s. Otherwise, the system performed asexpected.An improved AFSS test article flew on the SpaceX Falcon 1 from the Kwajalein/Reagan Test Siteon March 21, 2007. The test item consisted of a single chassis with redundant flight processors, acustom-built voting circuit, a power supply module, and a GPS receiver. An externally mounted GPSreceiver and a 10-W Low-Cost Tracking and Data Relay System (TDRS) Transceiver (LCT2) for aspace-based range demonstration were also flown.The LCT2 was to transmit the status messages fromone of the processors and the messages from the otherprocessor were transmitted in the vehicle telemetrystream. Unfortunately, a concern was raised onlaunch day that the LCT2 might interfere with thevehicle GPS, and the Falcon 1 launch managementteam decided to fly with the LCT2 powered off. Thismeant that data from only one of the processors wasavailable for postflight analysis.First AFSS sounding rocket test flight.Even with the loss of the LCT2 data, the AFSS metall the minimum success criteria. These includedperforming properly before the launch, maintainingat least one GPS solution, transmitting validnavigation data from at least one GPS receiver,transmitting mission rule evaluation status from atleast one processor for the entire flight, and evaluatingthe full set of mission rules on at least one processorfrom launch to orbit insertion (or end of flight).56 Range Technologies
Falcon 1 launch vehicle at liftoff.An anomaly in the navigation solution of the externally housed GPS receiver, caused whenmarginal satellites swapped in and out of track, led one processor to improperly flag first-stageburnout and second-stage ignition events. Because of a setup error, the system used the elapsedtime from second-stage ignition as the time reference for tabulated, moving-gate coordinatesinstead of time from launch. These errors caused the two processors to issue ARM/FIREcommands at different times. In the future, acceleration data from one or more IMUs will be usedfor in-flight ignition and burnout event detection. Despite these anomalies, the inability to use theLCT2, and the rocket’s failure to reach its desired orbit, the testing was a valuable experience andwill lead to an improved AFSS.Continuing efforts to improve the AFSS include making the chassis more rugged, formalizing therequirements and design, and adding a loosely coupled GPS/Inertial Navigation Solution (INS) toimprove the reliability of the AFSS sensor suite. A prototype of this GPS/INS was flown on anF-104 at Kennedy Space Center on November 8, 2007. The equipment was integrated on theF-104 and recovered undamaged, but the GPS receiver did not function properly for reasons stillbeing investigated. Consequently, the data collected was not sufficient to determine how theGPS/INS system performed. A second set of flights is planned for 2008.Contacts: Dr. James C. Simpson , NASA-KSC, (321) 867-6937; andRoger D. Zoerner , ASRC Aerospace, (321) 861-2960KSC Technology Development and Application 2006-200757
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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
Page 19 and 20: Initial results of the EDEM model o
Page 21 and 22: Contacts: Dr. Carlos I. Calle ,NASA
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
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 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
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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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