Structural Integrity Analysis And Verification for Aircraft Structures: Volume 2: Effects Of Compressive Loading On The Fatigue Crack Growth Rates Of 7075-T651 And 2024-T3 Aluminum Alloys.

Abstract

The purpose of this research was to determine the effects of constant amplitude high compressive stresses on the fatigue life of 7O75-T651 and 2024-T3 aluminum alloys. This project consisted of three components: finite element modeling/analysis, generation of fatigue crack growth data for AFGROW modifications, and verification testing. An elastic-plastic finite element analysis program (ZIP2D) was used to determine the stress field in the crack plane for the different testing conditions. Fatigue crack growth data from center-notched, through-cracked panels were collected for both alloys at several loads and stress ratios, and these data were used to modify tabular crack growth data for the AGROW program. Center-notched and surface-cracked specimens were then tested to verify AFGROW predictions (with updated tabular data) for crack shape and fatigue lifetimes.

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Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1996
Accession Number
ADA327868

Entities

People

  • J. A. Harter

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Alloys
  • Aluminum
  • Aluminum Alloys
  • Crack Tips
  • Curvature
  • Elements
  • Finite Element Analysis
  • Fracture (Mechanics)
  • Geometry
  • Low Humidity
  • Mechanics
  • Residual Stress
  • Stress Intensity Factors
  • Stress Strain Relations
  • Structural Integrity
  • Verification

Readers

  • Business Analytics
  • Materials Science (Mechanical Engineering).