On the Determination of a Scatter Factor for Fatigue Lives Based on the Lead Crack Concept

AUTOR(ES)

Siqueira, Adriano Francisco, Baptista, Carlos Antonio Reis Pereira, Molent, Loris

FONTE

J. Aerosp. Technol. Manag.

DATA DE PUBLICAÇÃO

2013-06

RESUMO

ABSTRACT: The lead crack concept is adopted as the basis for a new fatigue lifeing method using the safe life philosophy. As part of its management strategy, a full-scale fatigue test is conducted to identify high-risk locations in the airframe, and for each item the time for retirement or structural repair is dictated by the safe life limit. A scatter factor is defined to account for the scatter in the material fatigue performance. The fatigue life variation of any given region of aircraft metallic structures is assumed to primarily correlate to the distribution of the equivalent pre-crack size of the fatigue crack initiators. By assuming that the sizes of these crack initiators are independent from each other, the present paper estimates the scatter factor by calculating safe life limit based on known growth characteristics of critical cracks.

Documentos Relacionados

• Estimation of fatigue lives of fly ash modified dense bituminous mixtures based on artificial neural networks
• DEVELOPMENT OF AN ANALYTICAL METHOD FOR THE DETERMINATION OF LEAD BASED ON LOCAL SURFACE PLASMON RESONANCE OF SILVER NANOPARTICLES
• On the prediction of fatigue crack retardation using Wheeler and Willenborg models
• Concept of a Maneuvering Load Control System and Effect on the Fatigue Life Extension
• Fatigue degradation strategies to simulate crack propagation using peridynamic based computational methods