ANALISIS TEGANGAN MAIN LANDING GEAR UNTUK AIRBUS HELICOPTER EC155 MENGGUNAKAN SOFTWARE CATIA V5R21

MUHAMMAD RAMADANI, SYECH (2018) ANALISIS TEGANGAN MAIN LANDING GEAR UNTUK AIRBUS HELICOPTER EC155 MENGGUNAKAN SOFTWARE CATIA V5R21. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

Landing Gear is an important component in the structure of the aircraft and helicopter EC155B. The type of landing gear used is Rectractable tricycle landing gear. The landing gear must be able to withstand Landing loads. So that there is no failure due to a weak structure. To find out the strength limit of the structure or Landing gear tension for the Airbus EC155 Helicopter, a structural analysis must be carried out. Modeling and analysis using CATIA V5R21 software. Namely using Workbench Part Design, Assembly Design, and Generative Structural Analysis. There is one load in this analysis, namely in Landing loads conditions. The analysis will be carried out in 3D. The amount of load that will be used is the maximum value of vertical reaction, drag, side load, combination of vertical reaction with drag, combination of vertical reaction and side load, and combination of the three. From the analysis, it was found that the entire structure of the landing gear model is safe. The maximum stress of the main landing gear is 227.71 MPa with a Margin of safety value of 4.9 N m2. So the Margin of safety value shows a positive value, so the structure of the landing gear can be declared to meet the requirements safe.

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