CAIBlsn9 - CAIB Analysis STS-107 In-Flight Damage...

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1/29/2007 1 STS-107 In-Flight Damage Assessment Process Review Orbiter Element Analyses CAIB Analysis
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1/29/2007 2 Debris Assessment Team Make-Up z Debris Assessment Team composed of over 37 engineers and technical Managers from NASA, USA, Boeing and SAIC STS-107 in-flight impact was an out-of-family problem and required NASA technical participation z Boeing Orbiter participation included: Analysis ITM, Analysis PM, TPS SSM, RCC SSM, Structural Analysis SSM, Aeroheating SSM, Thermal SSM and associated support personnel z USA Participation included: Analysis SAM (team lead), TPS SAM, RCC SAM, Systems Integration Manager and Flight Design Manager z NASA participation included: Thermal Asst. Branch Chief, Thermal / Loads Panel Chair, Aeroscience DCE, Wheel and Tire ROE, RCC z SAIC participation represented Safety for NASA z Photo Analysis group represented by SRB, ET and Systems Integration from KSC, MSFC and JSC
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1/29/2007 3 STS-107 Debris Assessment Chronology Sunday Monday Tuesday Wednesday Thursday Friday Saturday 16 Launch 17 Film Review Orbiter, Systems Integration (SI) and MER notified of debris (20 inches) impacting the Orbiter 18 SI performed preliminary trajectory analysis Orbiter performed preliminary tile damage analysis 19 20 Coordination meeting held to organize assessment team Action Rodney Rocha – investigate on- orbit photo 21 1 st Damage Assessment Team meeting 1 st Aeropanel meeting Rocha to investigate in-flight photo 22 2 nd Damage Assessment Team meeting Concluded no new entry profile offered significant benefit ET agreed with debris size 23 Orbiter and SI assessments results reviewed by Damage Assessment Team Notified that in- flight photo would not be approved USA & Boeing Orbiter Management review assessment 24 Damage Assessment Team presents results to pre-MMT (less case 6 results) Verbal summary given to MMT by MER manager Completed case 6 thermal evaluation 25 Completed case 6 stress evaluation Stress SSM Reviewed case 6 with USA SAM 26 Thermal / Structural Analysis SSMs report updated results to USA management and NASA DCE 27 Reported to MER manager that final case was completed and OK MER manager summarized results to MMT Issue considered closed 28 29 30 31 1
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1/29/2007 4
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1/29/2007 5
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1/29/2007 6 Area of Interest
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1/29/2007 7 2D Model – Simplified Wing Leading Edge System HRSI velocity 600-900 ft/s
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1/29/2007 8 6” 22” RCC 2.91” Insulation (Polyurethane foam) Sheet Stringer Skins Aluminum (2024-T81) Honeycomb Attached using 1/8” RTV 0.75” 0.04” Impact angle 10°- 90 ° velocity 600-900 ft/s 3D Model – Detail Wing Leading Edge System HRSI
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1/29/2007 9 Detail Wing Leading Edge System
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1/29/2007 10 Tile Installation RTV adhesive Filler bar Koropon-primed structure Strain isolation pad (SIP) Tile densified layer Reaction-cured glass (RCG) coating 0.045" Tile to Tile Gap
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CAIBlsn9 - CAIB Analysis STS-107 In-Flight Damage...

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