Fatigue in Adhesively Bonded Laminates.

Abstract

Fatigue crack propagation (FCP) and fatigue lifetime tests have been performed on several types of adhesively bonded aluminum alloy laminates. The laminate systems included several varieties of all-7075-T6(51) laminates--having 2, 4, 8 or 22 layers--as well as bi-material laminates combining 7075-T6 and 2024-T351 alloys. Among the conclusions of the study are: --FCP rates in crack divider laminates for which all layers are the same are comparable to those in the monolithic alloy. --FCP rates in bi-material 7075-T6/2024-T351 laminates are intermediate between those for the two alloys in monolithic form; over a considerable range of growth rates the bi-material laminates give FCP rates significantly lower than the averages of the two constituents. --Fatigue life-times of 7075-T6 8- and 22-layer laminates tested in tension-tension fatigue (R=0.1) are inferior to monolithic 7075-T6 alloy in either notched or unnotched forms; this is contrary to previous results for reversed bending.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1977
Accession Number
ADA049529

Entities

People

  • J. A. Alic

Organizations

  • Wichita State University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Adhesives
  • Air Force
  • Aluminum
  • Aluminum Alloys
  • Crack Propagation
  • Cracks
  • Engineering
  • Failure Mode And Effect Analysis
  • Fatigue Tests (Mechanics)
  • Fracture (Mechanics)
  • Geometry
  • Laminates
  • Materials
  • Measurement
  • Mechanics
  • Pressure Distribution
  • Stress Intensity Factors

Fields of Study

  • Materials science

Readers

  • Materials Science (Mechanical Engineering).
  • Structural Health Monitoring of Composite Structures.