ANALISIS KEKUATAN STRUKTUR WING AGRICULTURE
AIRPLANE DENGAN PAYLOAD 2720 POUNDS
MENGGUNAKAN SOFTWARE ANSYS
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
HANIF FANTONO, RIDHO
Subject
T Technology (General)
Datestamp
2024-05-06 02:42:27
Abstract :
An agriculture airplane is a type of aircraft flown over agricultural fields with the purpose of conducting the spraying of fertilizers, pesticides and hidroseeding. This research is an advanced stage of the previous study, which was the initial design phase. Therefore, this research will involve the modeling of structural design within the wing and the analysis of the strength of the structure. In the process of wing structural design, CATIA V5R21 software is utilized, and the structural analysis is conducted using ANSYS R17.1 software to obtain the wing structure's strength values base of failure criteria. The loading is carried out under maneuver condition 3.8 and a negative load factor limit of -1.5. The results obtained in this study indicate that the agricultural airplane with a payload of 2720 pounds has a wing configuration with a skin component (4.16 mm), 10 ribs (10,4), front spar (20,8 mm), rear spar (15,6 mm), leading edge (6,24 mm), trailing edge (5,2 mm). The maximum stress occurs in the first layer skin with a value of 171.6 MPa, and the total deformation takes place at the tip section with a value of 174.08 mm. Then, the maximum value of the wing failure criteria against value 0,7746 at load factor 3,8 so that the wing structure id declared safe according to Tsai-Hill calculation.
An agriculture airplane is a type of aircraft flown over agricultural fields with the purpose of conducting the spraying of fertilizers, pesticides and hidroseeding. This research is an advanced stage of the previous study, which was the initial design phase. Therefore, this research will involve the modeling of structural design within the wing and the analysis of the strength of the structure. In the process of wing structural design, CATIA V5R21 software is utilized, and the structural analysis is conducted using ANSYS R17.1 software to obtain the wing structure's strength values base of failure criteria. The loading is carried out under maneuver condition 3.8 and a negative load factor limit of -1.5. The results obtained in this study indicate that the agricultural airplane with a payload of 2720 pounds has a wing configuration with a skin component (4.16 mm), 10 ribs (10,4), front spar (20,8 mm), rear spar (15,6 mm), leading edge (6,24 mm), trailing edge (5,2 mm). The maximum stress occurs in the first layer skin with a value of 171.6 MPa, and the total deformation takes place at the tip section with a value of 174.08 mm. Then, the maximum value of the wing failure criteria against value 0,7746 at load factor 3,8 so that the wing structure id declared safe according to Tsai-Hill calculation.
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