Abstract
Fuselage is an airplane main body structure designed for accommodating the crew, passengers, and cargo. The fuselage of a modern aircraft is a semi-monocoque construction. Semi-monocoque structure is very efficient, it has a high strength to weight ratio, and it has design flexibility and can withstand local failure without total failure through load redistribution. One of the loading on fuselage is cabin pressure. In continuous operation airplane due to cabin pressure, damage often occur in the fuselage, for example on the stringer. Type of repair to deal with cases of damage to stringer needs to be analyzed. This study aims to determine the effect of angle thickness and fastener variations on the strength of repair stringer structure . The analysis stage by 3D modeling with CATIA software . Simulation of structural analysis in the form stress and calculating the Margin of Safety . The thicker of angle and the more number of fasteners in the web area and the flange used in the repair, the stress that occurs in each variation will decrease. Modeling the structure is safe against pressure loading.
Highlights
Fuselage is an airplane main body structure designed for accommodating the crew, passengers, and cargo
This study aims to determine the effect of angle thickness and fastener variations on the strength of repair stringer structure
Adaptive Design and Finite Element Analysis of Fuselage Floor Beam of an Aircraft, International Journal of Engineering Science & Management (IJESM)
Summary
Metode yang digunakan dalam penelitian ini adalah Finite Element Method (FEM). Penelitian ini dimulai dengan pemodelan dan analisis struktur menggunakan software CATIA, kemudian dari hasil analisis akan ditentukan respon struktur dalam bentuk tegangan maksimum. Langkah selanjutnya menghitung Margin of Safety (MS) untuk mengevaluasi pengaruh ketebalan angle dan variasi fastener yang digunakan terhadap kekuatan strukturnya. Metodologi penelitian yang digunakan untuk penyelesaian masalah pada penelitian ini digambarkan dalam diagram alir penelitian (gambar 1). 2.1 Struktur Repair Stringer Pada penelitian ini struktur yang akan dimodelkan adalah struktur stringer pada fuselage pesawat. Profil repair stringer dan section atau bagian-bagiannya terlihat pada gambar 2. Repair untuk stringer pada pesawat Boeing 737300 terdapat dalam SRM (Structure Repair Manual). Manual ini berisi mengenai jenis-jenis repair yang dilakukan untuk damage yang terdapat pada pesawat. Untuk repair yang dilakukan pada fuselage lebih spesifik ke stringer terdapat pada SRM 53-00-03.
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