ANALISIS STRUKTUR WING PESAWAT UDARA NIR AWAK (PUNA)
KARGO DENGAN PAYLOAD 500 KG MENGGUNAKAN
SOFTWARE ANSYS
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
NUR HIDAYAT, CANDRA
Subject
T Technology (General)
Datestamp
2024-04-25 03:57:19
Abstract :
In designing an aircraft, the strength of the structure is one of the most important things that must be considered and re-examined by the aircraft designer. PUNA cargo is a type of fixed wing aircraft that has missions in civil and military aviation. With this goal, PUNA cargo must have toughness in all conditions. One of the most important components is the wing, the wing structure must have a light and strong material, the carbon woven epoxy material has the advantage of being rigid and lightweight, has a high yield strength with a relatively low density value, the material is easy to obtain with many variations and also easy to shape as needed. The wing modeling process uses CATIA V5R21 software, and the wing structure analysis process uses ANSYS R17.1 software with import stages, engineering data, geometry, model, ansys composite prepost, setup, solution, and result. with the loading of manouvre condition and negative limit load factor with the fixed support on the chord root. The results of this study are wing configurations that are safe for use by aircraft, maximum stresses and also the value of the wing structure failure criteria using the Tsai-Hill method. The results of this study found that PUNA cargo with a payload of 500 kg has a wing configuration with skin components (3.12mm), 8 ribs (10.4mm), 2 spars (20.8mm), leading edge (5.2mm), and trailing. edge (1.56mm). The maximum stress value that occurs in the wing structure as a whole is located at the root of 125,37 Pa and the maximum total deformation is at the tip with a value of 0,013192 m. The maximum value of the wing failure criteria lies in the first 2 layers of rib with a value of 0,39636, the wing structure is said to be safe according to Tsai-Hill calculations.
In designing an aircraft, the strength of the structure is one of the most important things that must be considered and re-examined by the aircraft designer. PUNA cargo is a type of fixed wing aircraft that has missions in civil and military aviation. With this goal, PUNA cargo must have toughness in all conditions. One of the most important components is the wing, the wing structure must have a light and strong material, the carbon woven epoxy material has the advantage of being rigid and lightweight, has a high yield strength with a relatively low density value, the material is easy to obtain with many variations and also easy to shape as needed. The wing modeling process uses CATIA V5R21 software, and the wing structure analysis process uses ANSYS R17.1 software with import stages, engineering data, geometry, model, ansys composite prepost, setup, solution, and result. with the loading of manouvre condition and negative limit load factor with the fixed support on the chord root. The results of this study are wing configurations that are safe for use by aircraft, maximum stresses and also the value of the wing structure failure criteria using the Tsai-Hill method. The results of this study found that PUNA cargo with a payload of 500 kg has a wing configuration with skin components (3.12mm), 8 ribs (10.4mm), 2 spars (20.8mm), leading edge (5.2mm), and trailing. edge (1.56mm). The maximum stress value that occurs in the wing structure as a whole is located at the root of 125,37 Pa and the maximum total deformation is at the tip with a value of 0,013192 m. The maximum value of the wing failure criteria lies in the first 2 layers of rib with a value of 0,39636, the wing structure is said to be safe according to Tsai-Hill calculations.
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