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Transcript of Mellis.matt
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Matt MelisNASA Glenn Research Center
Cleveland Ohio
Lessons from Columbia
Ballistic Impact Dynamics
Project Management Challenge 2009Daytona Beach, Florida
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Matt MelisNASA Glenn Research Center
Cleveland Ohio
Contributions of Ballistic Impact Research inThe Columbia Accident Investigation
&NASA’s Return to Flight
Project Management Challenge 2009Daytona Beach, Florida
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A Brief Overview of the Shuttle Launch System
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A Brief Overview of the Shuttle Launch System
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A Brief Overview of the Shuttle Launch System
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A Brief Overview of the Shuttle Launch System
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A Brief Overview of the Shuttle Launch System
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The Columbia Accident
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On January 16 2003, Columbia’s leading edge was impacted by a piece of foam suspected to have separated from the external tank bipod ramp at 81 seconds into its launch.
Columbia was traveling at Mach 2.46, at an altitude of 65,860 feet. The foam was calculated to have hit the Orbiter at 700 – 800 feet per second
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Insulating Foam Separates from Bipod Ramp andImpacts Left Wing of Columbia
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Insulating Foam Separates from Bipod Ramp andImpacts Left Wing of Columbia
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Image from CAIB Report
Showing shuttle ramp and wing
BipodRamp
ImpactPoint
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The Bipod Ramp
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The Bipod Ramp
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Redesign of the External Tank Bipod Ramp
Old Design New Design
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The Orbiter Leading Edges
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Reinforced Carbon-Carbon (RCC) Panels Protect the Leading Edges of the Orbiter
22 panels per wing
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RCC Panels 6, 8 & 9 of Specific Interest
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RCC T-Seals Seal the Gap Between Panels
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Leading Edge Panel Used for Full Scale Tests
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Forensic Reconstruction
Establish Probable Cause
Support Findings with Full Scale Testing
Efforts of theColumbia Accident Investigation Board
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The Reconstruction Effort
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The Debris Field
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The Debris Hanger
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The Debris Hanger
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The Debris Hanger
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Reconstructing the Left Wing Leading Edges
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Reconstructing the Left Wing Leading Edges
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Panel 8 Found with Significant Spatter Deposition and Erosion
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Right Wing Leading Edges Exhibited No Significant Spatter
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The NASA Impact Analysis Development Effort
With the Explicit Finite Element Code LS DYNA
Boeing, NASA GRC, JSC, LaRCExtensive impact dynamics experience at Glenn & Langley
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• BX-250 External Tank foam characterization
• Develop finite element mesh of panels and T-seals
• Reinforced Carbon-Carbon characterization
• Demonstrate valid impact analysis capability with LS DYNA
Impact Analysis Development Effort
For the Accident Investigation
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LS DYNA Predicts Car Collisions
Courtesy of LSTC
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LS DYNA Predicts Fan Blade Containment
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SRB Aft Skirt Splashdown with TVC Upgrade Tank
LS DYNA Predicts Water Impacts
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The NASA Glenn Ballistic Impact Lab
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Large Vacuum Gun
The NASA Glenn Ballistic Impact Lab
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2 Inch Vacuum Gun
The NASA Glenn Ballistic Impact Lab
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BX-250 External Tank Foam Characterization
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No Vacuum708 ft/sec
Vacuum693 ft/sec
High Speed Video of 90 Degree Impacts
BX-250 External Tank Foam Characterization
Ballistic Research Supporting the Accident Investigation
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LS Dyna is an industry standard commercial finite element analysis code typically used to model impact events
LS DYNA Predicts 90 Degree
Foam Impact on Load Cell
LS DYNA - explicit finite element impact analysis
Ballistic Research Supporting the Accident Investigation
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LS DYNA Predicts 23 Degree Foam Impact on Load Cell
LS DYNA - explicit finite element impact analysis
Ballistic Research Supporting the Accident Investigation
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Reinforced Carbon-Carbon Characterization
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Ballistic Impact Tests on RCC Coupons
Ballistic Research Supporting the Accident Investigation
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Ballistic Impact Tests on RCC Coupons
Ballistic Research Supporting the Accident Investigation
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RCC Coupon Shows No Damage After 397 ft/sec Foam Impact
Ballistic Impact Tests on RCC Coupons
Ballistic Research Supporting the Accident Investigation
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Foam Fractures RCC coupon in half at 695 ft/sec
Ballistic Impact Tests on RCC Coupons
Ballistic Research Supporting the Accident Investigation
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400 ft/second Impact
700 ft/second Impact
Ballistic Impact Tests on RCC Coupons
Ballistic Research Supporting the Accident Investigation
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Full Scale Impact Analysis with LS Dyna
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Dyna - explicit finite element impact analysis
Full Scale Panel Analysis
Ballistic Research Supporting the Accident Investigation
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43,000 Panel Shell Elements147,000 Foam Brick Elements
Dyna - explicit finite element impact analysisBallistic Research Supporting the Accident Investigation
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Dyna - explicit finite element impact analysisBallistic Research Supporting the Accident Investigation
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Panel 6 Edge Impact Case
Dyna - explicit finite element impact analysisBallistic Research Supporting the Accident Investigation
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Dyna - explicit finite element impact analysisBallistic Research Supporting the Accident Investigation
Panel 6 Edge Impact Case RCC Damage
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The Full-Scale Testing Effort
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Tests conducted at Southwest Research InstituteOrbiter Leading Edge Full-Scale Tests
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Orbiter Leading Edge Full-Scale Tests
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Installation of internal high speed cameras
Orbiter Leading Edge Full-Scale Tests
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Leading edge panels mounted after camera installation
Orbiter Leading Edge Full-Scale Tests
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Phantom digital cameras set up inside of full scale test article
Orbiter Leading Edge Full-Scale Tests
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High intensity lights required both in and outside of test article
Orbiter Leading Edge Full-Scale Tests
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Orbiter Leading Edge Full-Scale Tests
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External View of RCC Panel 8 Test
Orbiter Leading Edge Full-Scale Tests
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Barrel View of RCC Panel 8 Test
Orbiter Leading Edge Full-Scale Tests
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External View of RCC Panel 8 Test
Orbiter Leading Edge Full-Scale Tests
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Internal View of
RCC Panel 8 Test
Orbiter Leading Edge Full-Scale Tests
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Post Impact of Panel 8
Orbiter Leading Edge Full-Scale Tests
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Latest Dyna Predictions Correlate with Panel 9 Test
Dyna – explicit finite element impact analysisAnalysis Supporting Full-Scale Tests
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LS DYNA Analysis of Panel 8 Full-Scale Test
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Return to Flight
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• Additional foams, ice, ablator material characterization
• Begin advance RCC model development (coating)
• Full development of analysis capability with LS DYNA
Impact Analysis Development Effort
For Return to Flight
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2 grams foam2054 ft/sec
2 grams foam2054 ft/sec
8 grams ice650 ft/sec
8 grams ice650 ft/sec
Impact Studies on RCC for Model ValidationBallistic Impact Research Supporting Return to Flight
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2 grams foam2371 ft/sec
2 grams foam2371 ft/sec
8 grams ice858 ft/sec
8 grams ice858 ft/sec
Impact Studies on RCC for Model ValidationBallistic Impact Research Supporting Return to Flight
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Impact Studies on RCC for Model ValidationBallistic Impact Research Supporting Return to Flight
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Aramis Displacement Measurement SystemPhotogrametric Technique Determines Full 3-D displacements
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Aramis Displacement Measurement System
Point Displacement vs Time Displacement Contour Plot
Photogrametric Technique Determines Full 3-D displacements
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Aramis Adapted to Full-Scale Wing Leading Edge Tests
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ARAMIS Validates LS-DYNA Analysis Models
Aramis Adapted to Full-Scale Wing Leading Edge Tests
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Full-Scale Leading Edge Test Setup with Aramis at SwRI
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Full Field Displacements of Wing Leading Edge Impact Test
Aramis Data Validates LS DYNA Analysis Predictions
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Aramis Indicated2100-2700 Microstrain
Gauge Indicated 2100 Microstrain
Note Much Higher Amplitude 2” From Gauge
Principle Strain Comparison to Bonded Gauges
Aramis Data Validates LS DYNA Analysis Predictions
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RT 455 ablator impact at approximately 300 ft/sec
Ballistic Impact Research Supporting Return to Flight
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NCFI foam impact at approximately 800 ft/sec
Ballistic Impact Research Supporting Return to Flight
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Tile Gap Filler Material Impact Testing
Ballistic Impact Research Supporting Return to Flight
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Tile Repair Putty Material Impact Testing
Ballistic Impact Research Supporting Return to Flight
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Ice Formations on External Tank
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Ice Research Supporting the Return to FlightHigh Density Ice (no air bubbles entrained)
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Identification of Ice Microstructure
Ice Research Supporting the Return to Flight
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Impact Testing of IceHard ice impact at approximately 800 ft/sec
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Hadland Camera Captures Fracture Wave Propagation700 ft per second ice impact 280,000 frames per second
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Cordin Camera Captures Fracture Wave Propagation600 ft per second ice impact at 480,000 frames per second
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Ice Impact Testing on Full Scale Leading Edge
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External Tank Impact Testing
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External Tank Impact Test Article with Acreage FoamBallistic Impact Research Supporting Return to Flight
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Orbiter Windows Impact Testing
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Orbiter Windows Testing at NASA GRC
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NCFI Foam Impact Test on Orbiter WindowBallistic Impact Research Supporting Return to Flight
Rear View
Side View
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Typical Aluminum Oxide Projectiles
Al3O2 Particles Measured and Weighed
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Stereo Microscope Used to Load Gun
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Tweezers Required to Place Particles in Gun Barrel
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70 degree, 127 ft/sec
90 degree 359 ft/sec
50 degree 118 ft/sec
Aluminum Oxide particles impact orbiter windows
Ballistic Impact Research Supporting Return to Flight
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July 26, 2005
The most photographed mission
Return to Flight
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Forward and Aft SRB Cameras on STS-121
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Chase Plane Video of STS-114 Launch
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Rendezvous Pitch Maneuver
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Orbiter Boom Sensor System
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Orbiter Boom Sensor System
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- The Columbia Accident Investigation Board Final Report
- The Challenger Launch Decision by Diane Vaughan
- Lessons from Everest: The Interaction of Cognitive Bias, Psychological Safety, and System Complexity by Michael Roberto. Obtain from Harvard Bussiness Online
Additional Reading
- To Engineer is Humanby Henry Petroski - Organization at the Limit
by William Starbuck andMoshe Farjoun