ANALISIS KEKUATAN TARIK DAN BENDING DENGAN
MENGGUNAKAN MATERIAL KOMPOSIT FIBERGLASS WR
EPOXY DAN FIBER CARBON EPOXY
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
RACHMATINO YUDIANA, ALPHARIO
Subject
T Technology (General)
Datestamp
2024-07-15 03:08:42
Abstract :
PUNA ( Pesawat Udara Nir Awak ) is a type of plane made for specific mission which is remotely controlled by radio wave, nowadays the usage of PUNA is implemented in various sector. PUNA has size, configuration and variation of character, thus attention in accurately designing, material testing and strength analysis becomes important also greatly needed when designing PUNA and comparing the material strength between composite fiber carbon and fiberglass WR. PUNA 5774-Trainer is a fixed wing aircraft with a slow flyer (training glider) character for flight monitoring missions with light material. Starting with the design process, and the process of comparing composite materials between fiber carbon and fiberglass WR, until the manufacturing process is carried out by collecting data from various sources, this data can be obtained by collecting data from literature studies, modeling and structural analysis, and determining tools and ingredients. The type of material used in PUNA skin is a composite material mixed with epoxy resin and fiber carbon with the vacuum bagging method. From material testing with the tensile test method, the average value obtained in the carbon fiberglass composite tensile test is: max load = 34,797.99 N, elastic modulus = 727,483 MPa, yield point = 1,282.79 Kgf / mm ^ 2, and yield strength of 74.637 Kgf / mm ^ 2, resulting in a tensile stress value of 556.768 MPa and the strain value is 0.759. Whereas for the bending test for carbon fiberglass composites the average value obtained is: max load = 634.03 N, elastic modulus = 10.020 MPa, yield point = 15.26 Kgf / mm ^ 2 resulting in a stress value of 585.2578546 MP. After this process, the next step is the manufacturing process.
PUNA ( Pesawat Udara Nir Awak ) is a type of plane made for specific mission which is remotely controlled by radio wave, nowadays the usage of PUNA is implemented in various sector. PUNA has size, configuration and variation of character, thus attention in accurately designing, material testing and strength analysis becomes important also greatly needed when designing PUNA and comparing the material strength between composite fiber carbon and fiberglass WR. PUNA 5774-Trainer is a fixed wing aircraft with a slow flyer (training glider) character for flight monitoring missions with light material. Starting with the design process, and the process of comparing composite materials between fiber carbon and fiberglass WR, until the manufacturing process is carried out by collecting data from various sources, this data can be obtained by collecting data from literature studies, modeling and structural analysis, and determining tools and ingredients. The type of material used in PUNA skin is a composite material mixed with epoxy resin and fiber carbon with the vacuum bagging method. From material testing with the tensile test method, the average value obtained in the carbon fiberglass composite tensile test is: max load = 34,797.99 N, elastic modulus = 727,483 MPa, yield point = 1,282.79 Kgf / mm ^ 2, and yield strength of 74.637 Kgf / mm ^ 2, resulting in a tensile stress value of 556.768 MPa and the strain value is 0.759. Whereas for the bending test for carbon fiberglass composites the average value obtained is: max load = 634.03 N, elastic modulus = 10.020 MPa, yield point = 15.26 Kgf / mm ^ 2 resulting in a stress value of 585.2578546 MP. After this process, the next step is the manufacturing process.
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