ANALISIS KEKUATAN TARIK DAN BENDING MATERIAL
KOMPOSIT SANDWICH FIBERGLASS WR DENGAN CORE
LANTORSORIC
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
SYAFRI PRATAMA, FANDI
Subject
T Technology (General)
Datestamp
2024-08-02 04:26:52
Abstract :
Airplanes consist of various components and structures that are arranged into a single unit that has limited structural strength. The design of every part of the aircraft must be considered as detailed and accurate as possible in order to produce efficient and durable aircraft components and structures. The strength of the fuselage structure is very important in the manufacture of aircraft, including the manufacture of UAV aircraft, the strength of the fuselage structure changes when the type of material and the thickness of the material changes. Therefore, testing is needed to determine the ability of a material that is applied in the manufacture of aircraft. The PUNA 5774 Trainer fuselage is designed using WR Fiberglass sandwich composite material with lantorsoric as the core. Testing the strength of the material is carried out by using the tensile test and bending test methods. The process of making test specimens is carried out by the hand layup method. The results of testing the composite sandwich material with lantorsoric as the core, the average stress value for the Tensile Test is 1.005x102 Mpa and the modulus of elasticity is 1.165x103 Mpa and from the bending test the average value for Flexural Strength is 21,32 Mpa and Flexural Modulus of 2,704 GPa
Airplanes consist of various components and structures that are arranged into a single unit that has limited structural strength. The design of every part of the aircraft must be considered as detailed and accurate as possible in order to produce efficient and durable aircraft components and structures. The strength of the fuselage structure is very important in the manufacture of aircraft, including the manufacture of UAV aircraft, the strength of the fuselage structure changes when the type of material and the thickness of the material changes. Therefore, testing is needed to determine the ability of a material that is applied in the manufacture of aircraft. The PUNA 5774 Trainer fuselage is designed using WR Fiberglass sandwich composite material with lantorsoric as the core. Testing the strength of the material is carried out by using the tensile test and bending test methods. The process of making test specimens is carried out by the hand layup method. The results of testing the composite sandwich material with lantorsoric as the core, the average stress value for the Tensile Test is 1.005x102 Mpa and the modulus of elasticity is 1.165x103 Mpa and from the bending test the average value for Flexural Strength is 21,32 Mpa and Flexural Modulus of 2,704 GPa
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