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Space Shuttle
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Image
Published: 01 November 2010
Image
Published: 01 November 2010
Image
Published: 01 November 2010
Fig. 21.13 Coating sequence for space shuttle carbon-carbon parts. Carbon-carbon (C-C), silicon carbide (SiC), tetraethylortho-silicate (TEOS)
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Image
Published: 01 October 2012
Image
Published: 01 October 2012
Fig. 11.12 Thermal protection system materials for the U.S. Space Shuttle. More than 30,000 ceramic tiles are included in the system. Other materials making up the system are reinforced carbon-carbon composites (44 panels and the nose cap) and 333 m 2 (3581 ft 2 ) of felt reusable surface
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Image
Published: 01 October 2012
Image
Published: 01 October 2012
Fig. 11.20 Coating sequence for Space Shuttle carbon-carbon (C-C) parts. TEOS, tetraethylorthosilicate. Source: Ref 11.1
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Image
Published: 01 August 2005
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Published: 01 January 2000
Fig. 64 Hydrogen embrittlement failure of a 300 M steel space shuttle orbiter nose landing gear steering collar pin. The pin was heat treated to a 1895-MPa (275 ksi) strength level. The part was plated with chromium and titanium-cadmium. (a) Pin showing location of failure (actual size). (b
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in Aerospace Applications—Example Fatigue Problems
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Image
in Aerospace Applications—Example Fatigue Problems
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Fig. 10.2 Comparison of fatigue regimes encountered in the Space Shuttle Main Engines (SSMEs) and that encountered in aeronautical gas turbine engines
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Image
in Aerospace Applications—Example Fatigue Problems
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Image
Published: 30 June 2023
Large tanks constructed for the Space Shuttle required the development of weldable alloys with excellent strength, toughness, and fatigue resistance at room and cryogenic temperatures
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Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 July 2009
DOI: 10.31399/asm.tb.fdmht.t52060231
EISBN: 978-1-62708-343-0
... aerodynamic excitation of preburner fuel nozzles in Space Shuttle Main Engines by inserting spacers to limit nozzle tip displacement Fig. 10.14 Root-attachment area of second-stage high-pressure fuel turbopump turbine blade indicating location (point A ) of persistent fatigue cracking...
Abstract
This chapter explains how the authors assessed the potential risks of creep-fatigue in several aerospace applications using the tools and techniques presented in earlier chapters. It begins by identifying the fatigue regimes encountered in the main engines of the Space Shuttle. It then describes the types of damage observed in engine components and the methods used to mitigate problems. It also discusses the results of analyses that led to changes in design or approach and examines fatigue-related issues in turbine engines used in commercial aircraft.
Image
Published: 01 November 2011
Fig. 6.21 Friction stir weld process development tool at the Marshall Space Flight Center shown with an 8.2 m (27 ft) diameter barrel segment of the 2195 Al-Li external tank for the Space Shuttle at the National Aeronautics and Space Administration (NASA) Michoud Assembly Facility in New
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Image
Published: 01 October 2012
Fig. 2.45 Friction stir weld process development tool at the Marshall Space Flight Center (MSFC) shown with an 8.2 m (27 ft) diameter barrel segment of the 2195 aluminum-lithium Space Shuttle. National Aeronautics and Space Administration (NASA) Michoud Assembly Facility in New Orleans
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Image
in Aerospace Applications—Example Fatigue Problems
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Fig. 10.13 Near-term fix to prevent aerodynamic excitation of preburner fuel nozzles in Space Shuttle Main Engines by inserting spacers to limit nozzle tip displacement
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in Aerospace Applications—Example Fatigue Problems
> Fatigue and Durability of Metals at High Temperatures
Published: 01 July 2009
Fig. 10.5 Half-cycles of thermal strain-induced hysteresis. (a) Thermal down-shock followed by equilibrium temperatures. (b) Thermal up-shock following Space Shuttle Main Engine firing
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Image
Published: 01 August 1999
Fig. 7 Crevice corrosion of an anodized aluminum alloy 2024-T851 window frame from the space shuttle Challenger . Corrosion occurred along both thermal and environmental sealing grooves. (a) Window frame showing locations of corrosion (arrows). (b) Enlargement of (a) showing corrosion
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Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 August 2005
DOI: 10.31399/asm.tb.horfi.t51180001
EISBN: 978-1-62708-256-3
... is a failure because these items are now space debris. Like the ISS and the Space Shuttle, the space debris also travels at 7,823 m/s (17,500 mph)—though not necessarily in the same direction or at the same altitude. We can currently track more than 9000 pieces of such debris, and we just keep adding...
Abstract
Failure investigation is an integral part of any design and manufacturing operation, providing critical information to solve manufacturing problems and assist in redesigns. This chapter addresses several aspects of failure investigation, beginning with the challenges of organizing such efforts and the need to define a clear and concise goal, direction, and plan prior to the investigation. It covers the causes of failure and the training and education organizations require to understand and prevent them. The chapter emphasizes the importance of discovering the root cause of failures, and uses examples to explain the factors involved and how to recognize them when the first appear.
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