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Published: 01 September 2011
Fig. 8.10 NASA short-beam compression test fixture. Source: Ref 8.50 More
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Published: 01 May 2018
FIG. 8.16 Destiny, NASA’s laboratory module for U.S. research payloads aboard the International Space Station, was built by the Boeing Company. Source: NASA. More
Image
Published: 01 December 1995
Fig. 13-26 Hold down column pedestals that support NASA’s shuttles and solid rocket boosters at launch site More
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 More
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 More
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Published: 01 September 2011
Fig. 9.27 Typical analog test specimens for characterization and aging. JANNAF: Joint Army, Navy, NASA, Air Force More
Book Chapter

Series: ASM Technical Books
Publisher: ASM International
Published: 01 December 2000
DOI: 10.31399/asm.tb.htgpge.t67320189
EISBN: 978-1-62708-347-8
... of Automotive Engineers , 1973 10.4271/730580 • Townsend D.P. and Zaretsky E.V. , “Effect of Shot Peening on Surface Fatigue Life of Carburized and Hardened AISI 9310 Spur Gears,” NASA Report TP-2047 , NASA Lewis Research Center , Cleveland, OH , 1982 • Townsend D.P...
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Published: 01 June 1983
Figure 7.26 Ultimate tensile strengths as a function of temperature for CTFE, PET, PC ( Schramm et al., 1973 ), and NASA Resin 2 ( Soffer and Molho, 1967 ). More
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Published: 01 December 2015
Fig. 9 Damage to Monel alloy after fretting in air at room temperature for (a) 1000 cycles and (b) 5 × 10 4 cycles. Courtesy of R.C. Bill, NASA Lewis Research Center More
Image
Published: 01 June 1988
Fig. 2.6 Reference depth for common materials as a function of frequency. From A. F. Leatherman and D. E. Stutz, “Induction Heating Advances: Application to 5800 F,” NASA Report SP-5071, National Aeronautics and Space Administration, Washington, 1969 ( Ref 4 ) More
Image
Published: 01 June 1988
Fig. 2.10 Relationship between relative efficiency and critical frequency. From A. F. Leatherman and D. E. Stutz, “Induction Heating Advances: Application to 5800 F,” NASA Report SP-5071, National Aeronautics and Space Administration, Washington, 1969 ( Ref 4 ) More
Image
Published: 01 December 2015
Fig. 11 Effect of relative humidity on fretting damage to high-purity nickel. Damage produced after 3 × 10 5 cycles in (a) dry air and (b) saturated air. See also Fig. 10 . Courtesy of R.C. Bill, NASA Lewis Research Center More
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Published: 01 June 1988
Fig. 2.9 Critical frequency for efficient induction heating of several materials as a function of bar size. From A. F. Leatherman and D. E. Stutz, “Induction Heating Advances: Application to 5800 F,” NASA Report SP-5071, National Aeronautics and Space Administration, Washington, 1969 ( Ref 4 ) More
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Published: 01 December 2015
Fig. 13 Titanium surfaces fretted at 650 °C (1200 °F) after 10 5 cycles. The formation of a tough, thick oxide layer at this temperature decreased the amount of damage (compare with Fig. 12 ). (a) Overall view. (b) Closeup of central region. Courtesy of R.C. Bill, NASA Lewis Research Center More
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Published: 01 December 2015
Fig. 10 Effect of relative humidity on fretting damage to high-purity iron tested in air. (a) Dry air. (b) 10% relative humidity. (c) 35% relative humidity. (d) Saturated air. All specimens shown after 3 × 10 5 cycles. See also Fig. 11 . Courtesy of R.C. Bill, NASA Lewis Research Center More
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Published: 01 December 2015
with Fig. 13 . Courtesy of R.C. Bill, NASA Lewis Research Center More
Series: ASM Technical Books
Publisher: ASM International
Published: 01 December 2000
DOI: 10.31399/asm.tb.htgpge.9781627083478
EISBN: 978-1-62708-347-8
Image
Published: 01 March 2006
between fatigue life and plastic strain range. (d) Subsequent NASA data (unpublished on A-286, 34% cold-rolled and aged) showing linearity of the Manson-Coffin line More
Series: ASM Technical Books
Publisher: ASM International
Published: 01 June 1983
DOI: 10.31399/asm.tb.mlt.t62860343
EISBN: 978-1-62708-348-5
Series: ASM Technical Books
Publisher: ASM International
Published: 01 July 2009
DOI: 10.31399/asm.tb.fdmht.t52060043
EISBN: 978-1-62708-343-0
... Administration (NASA) contract to evaluate SRP concepts on ultrahigh-temperature materials under ultrahigh vacuum ( Ref 3.6 ). Grain-boundary migrations were decorated by the voids left in their wake. Fig. 3.10 Grain-boundary migration for tantalum alloy T-111 in ultrahigh vacuum in CC-type loading cycle...