Accession Number:

ADA175110

Title:

Assessment of Damage Tolerance Requirements and Analysis. Volume 1. Executive Summary

Descriptive Note:

Final technical rept. Sep 1982-Nov 1985

Corporate Author:

FAIRCHILD INDUSTRIES INC FARMINGDALE NY FAIRCHILD-REPUBLIC DIV

Personal Author(s):

Report Date:

1986-09-01

Pagination or Media Count:

42.0

Abstract:

A structural test program of a 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 fightertrainer and bombercargo-type loading spectra, respectively, and to constant amplitude loading spectrum. A total of 72 specimens were tested. The test results were correlated with analytical predictions using the crack growth method and combined method. As a result of this study, a 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 predicting crack growth and crack initiation time. This volume, Volume I of a five-volume report, presents an Executive Summary of the entire program.

Subject Categories:

  • Attack and Fighter Aircraft
  • Couplers, Fasteners and Joints
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE