A material selection method based on material properties and operating parameters
Wolf Elber, John R. Davidson, Langley Research Center, United States. National Aeronautics and Space Administration
National Aeronautics and Space Administration, 1973 - Technology & Engineering - 12 pages
The influence of strength, fracture toughness, and crack growth resistance on the design stress level has been determined from a mathematical model of crack growth and failure. The results show that to select materials properly, the operating parameters of desired life and initial flaw size must be considered simultaneously with the material properties. To do this, a method for constructing an operating surface is derived, discussed, and illustrated.
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aluminum aluminum alloy annealed CALCULATED LIVES conditions requiring long considered simultaneously constant-amplitude crack length aQ crack-growth constant crack-growth equation crack-growth exponent crack-growth properties crack-growth rate data crack-growth resistance cycles D6AC design conditions requiring design operating conditions design stress level dominant material properties Elber and John equa equation 11 fatigue crack-growth Figure 1(a Fracture Mechanics fracture toughness given initial flaw going toward point growth and failure half-length improve NDI influence of strength initial flaw size initial flaw sizes Langley Research Center lives and short loading MATERIAL SELECTION METHOD operating parameters operating surface parameters of desired particular values Performing Organization PROPERTIES AND OPERATING region represents design conditions represents design operating requiring long lives rial S-N curve sacrifice life requirement select materials properly SELECTION METHOD BASED short initial flaw short lives shown in figure stress intensity range stress-to-density ratio surface represents titanium alloy ultimate strength unflawed material wide panel Wolf Elber yield strength