Durability Methods Development. Volume 7. Phase 2. Documentation

Abstract

A statistically-based durability analysis methodology is evaluated, refined and demonstrated in this report for advanced metallic airframes. This methodology can be used to: (1) analytically assure the U.S. Air Force's durability design requirements, (2) evaluate durability design tradeoffs, and (3) evaluate structural maintenance requirements and user options affecting life-cycle costs. The methodology accounts for initial fatigue quality, crack growth accumulation in a population of structural details, load spectra and structural properties. Analytical procedures and guidelines are developed and described for quantifying the extent of damage due to fatigue cracking in structural details as a function of service time and design variables. An initial fatigue quality model is described and discussed. This model is based on the time-to-crack-initiation (TTCI) and the equivalent initial flaw size (EIFS) concepts and a deterministic crack growth power law. An experimental test program and the resulting fractographic data for cracks in clearance-fit fastener holes are described and discussed.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1984
Accession Number
ADA142400

Entities

People

  • D. E. Gordon
  • J. N. Yang
  • M. Shinozuka
  • S. D. Manning
  • S. M. Speaker

Organizations

  • General Dynamics

Tags

Communities of Interest

  • Air Platforms
  • C4I

DTIC Thesaurus Topics

  • Air Force
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Computer Programs
  • Databases
  • Distribution Functions
  • Fatigue Cracking
  • Fracture (Mechanics)
  • Government Procurement
  • Information Science
  • Life Cycle Costs
  • Materials
  • Mechanics
  • Probability Density Functions
  • Statistical Analysis
  • Wing Boxes

Readers

  • Life Cycle Cost Analysis
  • Structural Health Monitoring of Composite Structures.