ANALISIS DAN PEMILIHAN DESAIN STRUKTUR KOMPOSIT MAIN LANDING GEAR PUNA WULUNG MENGGUNAKAN METODE ELEMEN HINGGA

PERMANA, ANDRIAN (2016) ANALISIS DAN PEMILIHAN DESAIN STRUKTUR KOMPOSIT MAIN LANDING GEAR PUNA WULUNG MENGGUNAKAN METODE ELEMEN HINGGA. Skripsi thesis, Institut Teknologi Dirgantara Adisutjipto.

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Abstract

PUNA is an aircraft that is being developed by the Agency for the Assessment and Application of Technology (BPPT) which is useful for meeting the needs of the TNI/POLRI Defense Equipment and surveillance functions. One of the important parts of PUNA is the main landing gear which functions to withstand the aircraft load. Due to the dynamic nature of the aircraft, the main landing gear must be really strong, so an analysis needs to be carried out to anticipate failures that occur in the structure. In addition, because it must have a light and strong structure when experiencing a load, the use of composite materials is the optimal structural solution. In selecting the composite structure design to be applied, it can be done by comparing two or more designs with different composite materials to determine the failure indices, strength (when receiving a load) and mass (which is lighter). Furthermore, the most reliable design can be determined to be applied. The method used in the design analysis of the PUNA Wulung main landing gear structure is the Finite Element Method (FEM) which is one of the numerical methods to solve various engineering problems so that the results of the stress approximation that occurs in a structure are obtained. The FEM software used in this analysis process is MSC Patran / Nastran 2012 and in the analysis process, variations in materials are applied to the model created. Model 1 uses carbon epoxy material and model 2 uses Eglass epoxy material which is then analyzed and tested for convergence (for validation) to obtain stress values ​​and failure indices. The results of the analysis showed that the maximum stress value in model 1 (3.8 kg) occurred in layer 23 with a failure indices value of 0.876 and the maximum stress value in model 2 (4.1 kg) occurred in layer 23 with a failure indices value of 3.467. Thus, model 1 is more reliable than model 2 to be applied to the PUNA Wulung main landing gear structure

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