Accession Number:

AD0632123

Title:

A METHOD FOR ESTIMATING THE FATIGUE LIFE OF 7075-T6 ALUMINUM ALLOY AIRCRAFT STRUCTURES

Descriptive Note:

Technical Report

Corporate Author:

GENERAL DYNAMICS SAN DIEGO CA SAN DIEGO

Personal Author(s):

Report Date:

1965-12-01

Pagination or Media Count:

73.0

Abstract:

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.

Subject Categories:

  • Aircraft
  • Metallurgy and Metallography
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE