DESAIN INTERNAL STRUKTUR DAN ANALISIS STATIK
STRUKTUR PESAWAT UAV CARGO-X
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Surya Atmaja, Yosef
Subject
T Technology (General)
Datestamp
2024-07-25 02:46:35
Abstract :
In line with the rapid progress of modernization, human?s need of technology is growing. It goes along with Aviation which always expands their sophisticated technology to help humans achieve their goals; not only for the purpose of human?s transportation, but also for goods delivery. UAV cargo plane is expected to be beneficial in many sectors, especially in producing a faster, low-cost, and efficient goods delivery. According to the mission, designing UAV cargo plane requires a specific internal aircraft frame design and analysis; to be able to measure its Equivalent Stress and its Maximum Deformation as the indicator of the aircraft frame?s strength and endurance. Indeed, it is important to ensure the UAV cargo plane could fly with maximum quality without failure. The process of designing internal aircraft frame includes choosing the right material and determining both geometrical and configuration of the aircraft parts which later will be analyzed. Then, the aircraft frame testing process is done by creating aero-modeling using CATIA software. The aero?modeling is done for wing section, fuselage, and empennage. Each part is analyzed using ANYSYS software to measure the value of Maximum Equivalent Stress and Maximum Deformation while loaded, with the load factor of 3. When the Margin of Safety result of the analysis is positive, then the aircraft frame is considered safe. The result of the aircraft frame testing indicates that the biggest distribution of Maximum Equivalent Stress happens on the wing section, specifically at the root wing with the value of 174.72 MPa. While on the fuselage, the value is 6.3808 × 10-2 MPa. As for the empennage, the value is 0.85493 MPa. Maximum Deformation happens on the wing section is 4.1568, on the fuselage is 207.4378, while on the empennage is 1052.8874. Both results indicate that, in general, the aircraft frame for UAV cargo plane is safe.
In line with the rapid progress of modernization, human?s need of technology is growing. It goes along with Aviation which always expands their sophisticated technology to help humans achieve their goals; not only for the purpose of human?s transportation, but also for goods delivery. UAV cargo plane is expected to be beneficial in many sectors, especially in producing a faster, low-cost, and efficient goods delivery. According to the mission, designing UAV cargo plane requires a specific internal aircraft frame design and analysis; to be able to measure its Equivalent Stress and its Maximum Deformation as the indicator of the aircraft frame?s strength and endurance. Indeed, it is important to ensure the UAV cargo plane could fly with maximum quality without failure. The process of designing internal aircraft frame includes choosing the right material and determining both geometrical and configuration of the aircraft parts which later will be analyzed. Then, the aircraft frame testing process is done by creating aero-modeling using CATIA software. The aero?modeling is done for wing section, fuselage, and empennage. Each part is analyzed using ANYSYS software to measure the value of Maximum Equivalent Stress and Maximum Deformation while loaded, with the load factor of 3. When the Margin of Safety result of the analysis is positive, then the aircraft frame is considered safe. The result of the aircraft frame testing indicates that the biggest distribution of Maximum Equivalent Stress happens on the wing section, specifically at the root wing with the value of 174.72 MPa. While on the fuselage, the value is 6.3808 × 10-2 MPa. As for the empennage, the value is 0.85493 MPa. Maximum Deformation happens on the wing section is 4.1568, on the fuselage is 207.4378, while on the empennage is 1052.8874. Both results indicate that, in general, the aircraft frame for UAV cargo plane is safe.
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