Accession Number:

AD0702528

Title:

FRACTURE MECHANICS GUIDELINES FOR AIRCRAFT STRUCTURAL APPLICATIONS

Descriptive Note:

Final rept. Jan-Nov 1969

Corporate Author:

NORTHROP CORP HAWTHORNE CA AIRCRAFT DIV

Personal Author(s):

Report Date:

1970-02-01

Pagination or Media Count:

199.0

Abstract:

The document provides the guidelines, limitations, and modifications required to perform a structural, fracture analysis using Griffith-Irwin, fracture mechanics principles. It serves as an introduction to fracture mechanics for those personnel who are concerned with fracture strength estimates for aerospace structural applications. Illustrations and hypothetical examples are included which show how engineering solutions for critical crack size and fracture stress may be made. The critical stress intensity fracture toughness concept is used as a basic factor for the fracture analysis of materials. For most crack situations, a stress intensity factor can be computed which can be related to critical conditions and estimates made of critical crack lengths, stresses, and crack propagation behaviors. To provide a complete and accurate fracture analysis, the user is encouraged to become familiar with all aspects of the analysis and its limitations.

Subject Categories:

  • Aircraft
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE