Abstract
In this investigation, fatigue criterion was established to predict crack-initiation at the tip of a notch in aged hardening aluminum alloy. This criterion was used to predict the residual lifetime in aeronautical structures using concept of local stress at notch and subjected to constant amplitude loading characterized by mean stress. Charpy V-notch specimens were taken from sheet plate and the notch radius accurately machined at value of 0.2mm. The local stresses were determined numerical and validated analytically. In experimental investigation, the V-notched specimens were loaded in four point bending fatigue with a load ratio R=0.1 and variation in amplitude loading.
Highlights
GINTRODUCTION enerally, aeronautical structures are subjected to cyclic loading
Fatigue crack initiation criterion was established from notches in aged hardening aluminum alloy
This criterion was used to predict the residual lifetime in aeronautical structures subjected to constant amplitude loading using concept of local stress at notch
Summary
GINTRODUCTION enerally, aeronautical structures are subjected to cyclic loading. Discontinuities and notches in mechanical components and structures present a site of stress concentration resulting of external load that could be sites of crack initiation. Fatigue crack initiation criterion was established from notches in aged hardening aluminum alloy. Fatigue crack initiation; Notch; Finite element method; Stress field; Aluminum alloy.
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