Resumo (PT):
Abstract (EN):
Damage-tolerance is the main design approach for airframes, making possible weight savings
and structural integrity assurance in the presence of eventual damage resulting from
manufacturing or developed in service. The damage-tolerance approach relies upon databases
of fatigue and fracture properties, corrosion behavior, failure modes and non-destructive
inspection, particularly minimum detectable defect size and inspection intervals. When
inspection is impossible or multiple load paths are unavailable, then the older safe life design
approach needs to be used - that is the case of certain airframe details and of the landing gear.
The presentation will review the topic of fatigue of airframes highlighting issues as materials
choice (Al alloys including Al-Li, composites …), mixed mode crack propagation testing and
modelling, residual stresses and integral metallic structures, in the context of the evolution of
the applicable regulations of the Federal Aviation Administration (FAA) and European
Aviation Safety Agency (EASA). It constitutes an opportunity to up-date a previous plenary
lecture for another conference of the Associação Portuguesa de Análise Experimental de
Tensões (APAET), already in 2010: 8º Congresso Nacional de Mecânica Experimental,
Guimarães, [1].
Language:
English
Type (Professor's evaluation):
Scientific
Notes:
CNME2018 & TEMM2018: 11º Congresso Nacional de Mecânica Experimental em conjunto com 1ª Conferência Ibérica de Mecânica Teórica e Experimental e Materiais, Porto, Portugal), November 4-7, 2018. Published in: J. F. Silva Gomes, ed., ‘CNME2018 - Proceedings of the 1st Iberic Conference on Theoretical and Experimental Mechanics and Materials & 11th National Congress on Experimental Mechanics, Porto, Portugal, 4-7 November 2018, FEUP-INEGI, 2018.
No. of pages:
4