صورة الغلاف

Multiscale analysis of multiple cracks in aircraft fuselage

محفوظ في:
التفاصيل البيبلوغرافية
المؤلف الرئيسي: Oliveira, T. A. A.
تاريخ النشر: 2018
مؤلفون آخرون: Gomes, Gilberto, Evangelista Júnior, Francisco, Delgado Neto, Álvaro Martins
اللغة: eng
المصدر: Repositório Institucional da UnB
Download full: http://repositorio.unb.br/handle/10482/34233
الملخص: This paper consists of the multiscale analysis via Dual Boundary Element Method (DBEM) of fatigue life in riveted aircraft fuselage. First considers the macro analysis in which the fuselage panel is modeled at BemLab2D to obtain the Stress Intensity Factor (SIF) near a rivet. With the SIF, the stress field is then computed in a micro element composed of pre-established initial cracks and holes. This micro analysis was considered in three different positions (θ=0°, θ=45°, θ=90°) and analyzed the crack growth via Dual Boundary Element Method (DBEM) through BemCracker2D. As a result, there is a relationship between fatigue life (number of load cycles) and compliance of the edges of this micro element each crack increment.
الملخص:This paper consists of the multiscale analysis via Dual Boundary Element Method (DBEM) of fatigue life in riveted aircraft fuselage. First considers the macro analysis in which the fuselage panel is modeled at BemLab2D to obtain the Stress Intensity Factor (SIF) near a rivet. With the SIF, the stress field is then computed in a micro element composed of pre-established initial cracks and holes. This micro analysis was considered in three different positions (θ=0°, θ=45°, θ=90°) and analyzed the crack growth via Dual Boundary Element Method (DBEM) through BemCracker2D. As a result, there is a relationship between fatigue life (number of load cycles) and compliance of the edges of this micro element each crack increment.

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