Development of Statistical Fatigue Failure Characteristics of 0.125-Inch 2024-T3 Aluminum Under Simulated Flight-by-Flight Loading
Abstract
Thirty-two unique multidetail specimens were tested to develop a data base for investigating the statistical materials/structures fatigue failure characteristics of 2024-T3 aluminum alloy in the form of 0.225-in.-thick sheet. The test loading was a random-load, flight-by-flight loading block spectrum repeated to obtain crack initiation. Six different basic spectra, representative of cargo/transport or gust load flights, were applied to the specimens. Fatigue crack initiation was detected and controlled to a nominal crack length of about 0.04 in. from the edge of the hole by a painted crack detection circuit system. After detection of crack initiation, each hole was restored to an undamaged state by oversizing and coldworking. A statistical analysis of the data by previously developed maximum likelihood methods is presented for both scale and shape parameters of the log-normal and two- parameter Weibull distributions.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1974
- Accession Number
- ADA002310
Entities
People
- D. A. Rees
- J. P. Butler
Organizations
- Boeing