Limitations of Fatigue-Crack Research in the Design of Flight Vehicle Structures

R. Christensen; M. Harmon

doi:10.1520/STP47226S

SYMPOSIA PAPER Published: 01 January 1967

STP47226S

Limitations of Fatigue-Crack Research in the Design of Flight Vehicle Structures

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This paper surveys the current state of fatigue-crack research and the effect of this work on structural design. The subject areas discussed include: (1) fatigue-crack growth equations, (2) multiaxial strain effects, (3) temperature effects, (4) frequency effects, (5) anisotropic effects, (6) variable stress field effects, (7) fractography, (8) crack growth under random loads, and (9) critical elements and fracture modes. The current limited application of the available fatigue information to design is recognized. Practical objectives for fatigue research from the standpoint of structural design are itemized.

Author Information

Christensen, R., H.

Douglas Aircraft Co., Inc., Santa Monica, Calif.

Harmon, M., B.

Douglas Aircraft Co., Inc., Santa Monica, Calif.

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Details

Developed by Committee: E08

Pages: 5–24

DOI: 10.1520/STP47226S

ISBN-EB: 978-0-8031-6910-4

ISBN-13: 978-0-8031-6633-2

Limitations of Fatigue-Crack Research in the Design of Flight Vehicle Structures

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