A METHOD FOR ESTIMATING THE FATIGUE LIFE OF 7075-T6 ALUMINUM ALLOY AIRCRAFT STRUCTURES
GENERAL DYNAMICS SAN DIEGO CA SAN DIEGO
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The purpose of this investigation was to assess the validity of the Smith Cumulative Damage hypothesis for 7075-T6 aluminum alloy specimens and structures. It was found that the results of a single-amplitude test at short life can be used to estimate the stress at the point of failure, including residual stress. This permits using S-N data for axially loaded unnotched specimens to predict spectrum life. Excellent agreement was found between calculated and experimental lives of full-scale structures however, test lives of small specimens were consistantly shorter than predicted.
- Metallurgy and Metallography