Effects of Bonding Temperatures on Fatigue Crack Growth

Abstract

Changes in the crack growth behavior of 7075-T651 aluminum specimens which has been exposed to temperatures between 150 degrees and 355 degrees F (66 deg and 179 deg C) were evaluated. Specimens were fatigue tested at room temperature under flight-by-flight loading conditions. Results from these tests were then compared with data from the baseline (as received) material. Exposure to 250 deg F (121 deg C) or more produced a definite increase in speciment life, apparently due to a decrease in crack growth rates.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1983
Accession Number
ADA130396

Entities

People

  • John M. Potter
  • Rodney L. Wilkinson

Organizations

  • Wright Laboratory

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Space

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aerospace Craft
  • Air Force
  • Air Force Facilities
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Aluminum
  • Aluminum Alloys
  • Dynamics
  • Fatigue Tests (Mechanics)
  • Government Procurement
  • Governments
  • Materials
  • Security
  • Structural Integrity
  • Yield Strength

Readers

  • Structural Health Monitoring of Composite Structures.
  • Thermal Physics or Thermal Science.