REDUCTION OF THE ENDURANCE LIMIT AS A RESULT OF STRESS INTERACTION IN FATIGUE

Abstract

This paper presents the results of an investigation of the effects of stress interaction on fatigue life of aircraft structural materials subjected to randomized load spectra. All three materials: 2024 and 70?5 aluminum and SAE 4340 steel exhibit fatigue lives shorter than those predicted on the basis of the linear (Miner) damage rule. A quasi-linear rule is proposed with a variable, spectrum dependent. endurance limit producing safe life estimates; the dependence of the endurance limit on the stress spectrum and its resulting design inadequacy is shown. Tests were performed on high speed, programmed, rotating bending fatigue machines of special design.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1961
Accession Number
AD0258024

Entities

People

  • Robert A. Heller

Organizations

  • Columbia University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Aluminum
  • Fatigue Life
  • Fatigue Tests (Mechanics)
  • Government Procurement
  • Governments
  • Load Distribution
  • Materials
  • Mechanics
  • Physical Properties
  • Probability
  • Probability Density Functions
  • Spectra
  • Statistical Analysis
  • Steel
  • Tensile Strength

Readers

  • Plasma Physics / Magnetohydrodynamics
  • Structural Health Monitoring of Composite Structures.
  • Systems Analysis and Design