M. de Freitas  L. Reís  Lt. Cor. H. Gonçalo      

Anales de la Mecánica de la Fractura, nº 16 . 1999 . Pág. 113 -118
Ver (.pdf): Anales16-014

Resumen: This work presents parts of the damage tolerance assessment, on a criticallocation of an aircraft of the PoAF. Through in flight load measurements in critica! aircraft areas, normalized to 1 000 flight hours according to the usage of the aircraft, the load spectra was obtained and applied to specimens representíng the structure of the critica! location. The specimens are of plate structure with single side comer cracked hole. Results of crack growth under the spectrum loading are compared with crack growth predictions based on a cycle by cycle integration of Forman law with Wheeler retardation model and Elber/Nasgro law with closure loads calculated by the Newman equations and Corpus retardation model. Results show the applicability of crack growth predictions to the critica! aircraft components.

Localización: Torremolinos, Málaga

Secçäo de Projecto Mecfínico, Departamento de Engenharia Mecánica. Instituto Superior Técnico, Av. Rovisco País, 1049-001 Lisboa
Secçäo de Projecto Mecfínico, Departamento de Engenharia Mecánica. Instituto Superior Técnico, Av. Rovisco País, 1049-001 Lisboa
DMA, CLAFA, Força Aérea Portuguesa, Av. da Força Aérea, Alfragide, 2720 Amadora