2006-2007 - Kennedy Space Center Technology Transfer Office

More documents

Recommendations

Info

Crack Offset Measurement With the Projected Laser Target DeviceThe device and associated analysis methodology summarized in this report were developedDefect/Damage for the purpose of estimating the size of discontinuities in the surface of the foam thatLocationcovers the Space Shuttle External Tank. These surface offsets are thought to be due tosubsurface cracks in the foam insulation. The mathematical analysis and proceduredescribed here provide a method to quantity the dimensions of the crack offset in a directionperpendicular to the surface, making use of the projected laser target device (PLTD) tool and a laserline projector.The keys to the construction and use of the PLTD are the following geometrical design requirements:• Laser dots are on a square grid: length α on a side.• Laser beams are perpendicular to projected surface.• Beams are parallel out to the distance being projected.Figure 1. The projected laser target device (PLTD).Figure 2. Test setup, with a camera, PLTD, and a laser line projector.22 Spaceport Structures and Materials
The PLTD can be used to (1) calibrate fixed camerasof unknown magnification and orientation (far-fieldsolution); (2) provide equivalent calibration to multiplecameras, previously achieved only by the use of knowntarget points, for example, in 3‐D foreign-object debristracking on a fixed launch platform; (3) compute scalingfor conventional 2‐D images, and depth of field for 3‐Dimages (near-field solution); and (4) in conjunction witha laser line projector, achieve accurate measurements ofsurface discontinuity (cracks) in a direction perpendicularto the surface.Figure 5. Data extracted from image analysis (Figure 4) foroffset measurement.Figure 6. Analysis of data from Figure 5.Figure 3. Setup for measuring vertical offset of test objects.Figure 4. Image analysis of test in Figure 3.Figure 7. Plot of test data, showing measured offsetscompared to actual offsets.Contact: Dr. Robert C. Youngquist , NASA-KSC, (321) 867-1829Participating Organizations: NASA-KSC (Charles G. Stevenson) and ASRC Aerospace (Dr. John E. Lane)KSC Technology Development and Application 2006-200723
Page 5 and 6: ForewordSuccessful technology devel
Page 7 and 8: ContentsSpaceport Structures and Ma
Page 9 and 10: Contents (continued)Process and Hum
Page 11 and 12: IntroductionJohn F. Kennedy Space C
Page 13 and 14: Constellation SystemsSurfaceSystems
Page 15 and 16: Spaceport Structures and MaterialsK
Page 17 and 18: 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: Figure 2. A corrugated NiTi sheet e
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 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
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
show all

2006-2007 - Kennedy Space Center Technology Transfer Office

You also want an ePaper? Increase the reach of your titles

Delete template?

Save as template?