AN AIRCRAFT FUSELAGE FRACTURE ANALYSIS

Resumo

The continuum mechanics deals with the interaction between two bodies in order to analyze the
stresses in the domain due to the contact load. In this way, to compute the stresses, it is considered
each body as a semi-infinite in extent and having a plane surface. The Boundary Element Method
(BEM) appears as a numerical technique for evaluating this type of problem. Using this technique, the
boundary is discretized and the stresses are computed in the body domain. This paper consists of the
multiscale analysis via Dual Boundary Element Method (DBEM) of fatigue life of aircraft fuselage
plate. The macro analysis is evaluated through the stress field in the plate due to continuum
mechanics. With this stress field, a micro element, composed by different distribution of cracks, is
subjected to fatigue and analyzed by Dual Boundary Element Method (DBEM). This is accomplished
using the software BemCracker2D obtaining fatigue life data in each crack increment. For this,
advanced computational techniques were developed to evaluate the fracture mechanics behavior with
the purpose of ensuring the integrity and the good functioning of the fuselage during its design
lifespan.