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

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.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1965
Accession Number
AD0632123

Entities

People

  • Clarence R. Smith

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Abstracts
  • Air Force
  • Aircrafts
  • Aluminum Alloys
  • Engineering
  • Fasteners
  • Fatigue Life
  • Hardening
  • Horizontal Stabilizers
  • Materials
  • Mechanics
  • Residual Stress
  • Strain Hardening
  • Stress Strain Relations
  • Stresses
  • Test Fixtures
  • Yield Strength

Readers

  • Structural Health Monitoring of Composite Structures.
  • Theoretical Analysis.