Assessment of Damage Tolerance Requirements and Analysis. Volume 4. Raw Test Data

Abstract

Structural test program of typical aircraft structural configuration was conducted to assess the current Air Force damage tolerance design requirements defined in MIL-A-83444. The specimens, made of 2024-T3XX and 7075- T6XX, were subjected to randomized flight-by-flight spectra, representative of fighter/trainer and bomber/cargo type loading spectra, respectively, and to constant amplitude loading spectrum. A total of seventy-two (72) specimens were tested. The test results were correlated with analytical predictions using crack growth and crack initiation methods. As a result of this study, recommendation is provided to the validity of MIL-A-83444, to develop guidelines for selection of critical crack locations, and to assess the state-of-the-art analytical capabilities in prediction crack growth and crack initiation time.

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Document Details

Document Type
Technical Report
Publication Date
Mar 31, 1986
Accession Number
ADA170990

Entities

People

  • Meir Levy

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Force
  • Air Force Facilities
  • Aircrafts
  • Aluminum Alloys
  • Damage
  • Damage Tolerance
  • Dead Reckoning
  • Dynamics
  • Environment
  • Materials
  • Plastic Explosives
  • Security
  • Standards
  • Tensile Properties
  • Toughness
  • United States

Readers

  • Instructional Design and Training Evaluation.
  • Structural Health Monitoring of Composite Structures.