ANALISIS KEKUATAN STRUKTUR LOWER BULKHEAD FS
446.1 PADA PESAWAT F-16 A FIGHTING FALCON DENGAN
MENGGUNAKAN SOFTWARE CATIA V5R20
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
CAROLINA JOSE PEREIRA DA CONCEICAO, NOEMIA
Subject
T Technology (General)
Datestamp
2024-06-21 06:09:47
Abstract :
F-16A / TS-1603 is a fighter aircraft that is capable of maneuvering with agility in the air. In this maneuver all burden is borne by the structure of the aircraft. The load continues to be borne repeatedly by the F-16A / TS-1603 aircraft during operation, so it is necessary to inspect the aircraft structure. Inspection of the F-16A / TS-1603 aircraft structure is carried out at 400 flight hour intervals. At the time of inspection the aircraft had 5,989.6 hours of flying time and a crack at the lower bulkhead of Fs 446.1 with a crack length of 106.7 mm or 4.17 inches was found. So a change is made to the lower bulkhead structure Fs 446.1 because it cannot be repaired. Modeling and analysis was performed using CATIA V5R20 software. Analysis using CATIA V5R20 software is needed to obtain the value of the stress at the lower bulkhead crack Fs 446.1 and the replacement lower bulkhead Fs 446.1. From the results of these stresses it can be obtained the value of the margin of safety of the crack lower bulkhead Fs 446.1 and replacement lower bulkhead Fs 446.1. In the process of aircraft analysis, it is simulated in pull up and banking conditions. From the analysis using CATIA V5R20 software, it was found that the bulkhead structure according to TO and TCTO was safe. The highest margin of safety value at the time of pull-up was 145.98 crack lower bulkhead and 169.12 replacement lower bulkhead, and the highest margin of safety at banking was 282.54 crack lower bulkhead and 326.7 replacement lower bulkhead
F-16A / TS-1603 is a fighter aircraft that is capable of maneuvering with agility in the air. In this maneuver all burden is borne by the structure of the aircraft. The load continues to be borne repeatedly by the F-16A / TS-1603 aircraft during operation, so it is necessary to inspect the aircraft structure. Inspection of the F-16A / TS-1603 aircraft structure is carried out at 400 flight hour intervals. At the time of inspection the aircraft had 5,989.6 hours of flying time and a crack at the lower bulkhead of Fs 446.1 with a crack length of 106.7 mm or 4.17 inches was found. So a change is made to the lower bulkhead structure Fs 446.1 because it cannot be repaired. Modeling and analysis was performed using CATIA V5R20 software. Analysis using CATIA V5R20 software is needed to obtain the value of the stress at the lower bulkhead crack Fs 446.1 and the replacement lower bulkhead Fs 446.1. From the results of these stresses it can be obtained the value of the margin of safety of the crack lower bulkhead Fs 446.1 and replacement lower bulkhead Fs 446.1. In the process of aircraft analysis, it is simulated in pull up and banking conditions. From the analysis using CATIA V5R20 software, it was found that the bulkhead structure according to TO and TCTO was safe. The highest margin of safety value at the time of pull-up was 145.98 crack lower bulkhead and 169.12 replacement lower bulkhead, and the highest margin of safety at banking was 282.54 crack lower bulkhead and 326.7 replacement lower bulkhead
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