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Crack growth in ti-8al-1mo-1v with real-time and accelerated flight-by-flight loading LA. Imig

ASTM Symposia Papers Available online

ASTM Symposia Papers
Format:
Author/Creator:
Contributor:
Conference Name:
Language:
English
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Physical Description:
1 online resource (14 pages) illustrations, figures, tables
Place of Publication:
West Conshohocken, Pa. ASTM International 1976
Summary:
Crack growth in Ti-8Al-1Mo-1V was measured and calculated for real-time and accelerated simulations of supersonic airplane loading and heating. Crack-growth rates calculated on the assumption that an entire flight could be represented by a single cycle predicted the experimental rates poorly. Calculated crack-growth rates were slower than the experimental rates for all tests with flight-by-flight loading. For room-temperature accelerated tests, the calculated rates agreed well with the experimental rates; but the calculations became progressively less accurate for progressively more complex test conditions (tests that included elevated temperature). Calculations of crack growth using the crack-closure concept can probably be improved through study of crack-opening stresses using finite-element models that account for variable-amplitude loading, residual stresses, and temperature effects. The calculations of crack growth could also be improved through detailed studies of material properties and interactions among stress, temperature, and time as appropriate for the real-time operating conditions of a supersonic transport airplane
Notes:
  • Includes bibliographical references
  • Online resource; title from publisher's website, viewed December 19, 2016
Related Work:
American Society for Testing and Materials. Selected Technical Papers

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