Accession Number:

ADA053835

Title:

Fatigue Crack Propagation Analysis of Aircraft Structures.

Descriptive Note:

Master's thesis,

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF

Personal Author(s):

Report Date:

1978-03-01

Pagination or Media Count:

49.0

Abstract:

This thesis is a comparative study of aircraft fatigue life calculations based upon crack propagation and upon cumulative damage. The stress concentration factor, which supplies sufficient geometric information for Miners Law of cumulative damage, is found to not completely specify the geometry for the crack propagation approach. Effects on fatigue life of variations in initial crack length, plate width, hole size, and hole geometry for the same stress concentration factor have been investigated also both ordered and random load histories were used to compare the two approaches. Complete FORTRAN computer program input documentation for the IBM 36067 system has been included as an appendix to enable this thesis to serve as a users manual for CRACKS II, an Air Force crack propagation program for aircraft fatigue damage. Author

Subject Categories:

  • Aircraft
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE