Accession Number:

ADA207215

Title:

Advanced Durability Analysis. Volume 2. Analytical Predictions, Test Results and Analytical Correlations

Descriptive Note:

Final rept. Oct 1984-Feb 1989

Corporate Author:

GENERAL DYNAMICS FORT WORTH TX FORT WORTH DIV

Personal Author(s):

Report Date:

1989-02-27

Pagination or Media Count:

289.0

Abstract:

Advanced durability analysis design tools have been developed for metallic aircraft structures. These tools can be used to evaluate durability design requirements for functional impairments due to 1 excessive cracking and 2 fuel leakage ligament breakage. The methodology accounts for the initial fatigue quality variation of structural details, the crack growth accumulation for a population of structural details under specified design conditions and structural properties. Step by step procedures are provided. This volume is limited to the analytical methods, technical aspects, concepts and philosophy for the durability analysis of metallic aircraft structures. The methodology reflects a probabilistic approach, a fracture mechanics philosophy and both deterministic and stochastic crack growth methods. It can be used to predict the probability of crack exceedance at any service time andor the cumulative distribution of the time to reach any crack size. The methodology applies to the small crack size range associated with excessive cracking e.g., 0.05 and to large through-the-thickness cracks e.g., 0.5 - 0.75 associated with fuel leakageligament breakage. Keywords Durability, Fatigue, Equivalent initial flaw size, Initial fatigue quality, Crack initiation, Stochastic crack growth.

Subject Categories:

  • Aircraft
  • Test Facilities, Equipment and Methods
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE