Accession Number:

ADA031829

Title:

Numerical Computation of Stress Intensity Factors for Aircraft Structural Details by the Finite Element Method

Descriptive Note:

Final rept. Apr 1974-Apr 1975

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE AEROELASTIC AND STRUCTURES RESEARCH LAB

Report Date:

1976-05-01

Pagination or Media Count:

118.0

Abstract:

The results of a program of research involving application of the hybrid finite element method to fracture mechanics analyses of several typical aircraft structural details are presented. The performance properties of the specialized finite element building blocks are reviewed. Capabilities of the computer analysis codes are discussed with regard to valid parameter ranges, core storage requirements and execution times. Numerical results obtained from extended parameter studies are presented in the form of handbook charts. Suggestions are offered for future improvements and comments are made about the limits of applicability of the data base to airframe damage tolerance analysis.

Subject Categories:

  • Aircraft
  • Numerical Mathematics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE