Correlation of Fatigue Data for Aluminum Aircraft Wing and Tail Structures

Abstract

S-N curves are derived for aluminum wing and tail structures by fitting various regression models to 246 full-scale constant-amplitude fatigue test results from twelve types of aircraft structures. The derived curves were tested by comparing the predicted lives with actual test results of various aircraft structures fatigue tested to variable-amplitude loads spectra. More reliable predictions resulted from these derived S-N curves than from existing S-N curves.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1974
Accession Number
ADA008590

Entities

People

  • R. Hangartner

Organizations

  • National Research Council Canada

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircraft Industry
  • Aircraft Wings
  • Aircrafts
  • Airframes
  • Alloys
  • Aluminum
  • Aluminum Alloys
  • Fatigue Life
  • Fatigue Tests (Mechanics)
  • Frequency
  • Materials
  • Materials Laboratories
  • Mathematical Analysis
  • Mathematical Models
  • Models
  • Plastic Explosives
  • Test Methods

Readers

  • Regression Analysis.
  • Structural Health Monitoring of Composite Structures.