PENGARUH KETEBALAN SKIN TERHADAP KEKUATAN STRUKTUR SAYAP UAV V-SKY 14 NG MENGGUNAKAN METODE ELEMEN HINGGA
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Muhairi, Wahyuda
Subject
T Technology (General)
Datestamp
2024-02-15 08:25:55
Abstract :
UAV V-SKY 14 NG aircraft for monitoring road traffic on the ITD Adisutjipto campus complex and its surroundings has special capabilities in taking off and landing vertically or VTOL. However, from the latest design that has been completed by previous researchers, the material on the wing of the UAV V-SKY 14 NG still uses styrofoam which is a low-strength material. Therefore, in this study, the authors wanted to analyze the wing of the V-SKY 14 NG UAV with several variations of the material used, as well as adding variations in skin thickness. The material used in this study is a sandwich composite material configuration. For getting a stronger and better wing configuration. The object of research in this final project is the wing of the V-SKY 14 NG UAV aircraft, to analyze the strength of the structure using ANSYS software with the stages of engineering data, geometry, model, composite assembly prepost, setup, solution, and result. The loading that is carried out is the take-off load on the VTOL rod, maneuver conditions and torque load with the support of the stringer, core and layer skin to be able to determine the stress value that occurs and the safety level of the structure. The maximum stress of the maneuver load on the wing configuration with a skin thickness of 1.38 mm in Epoxy Carbon Woven (230 GPa) Wet material with a fiber angle of 0?-90? is 4.5458 MPa. The failure criterion value for the maneuver load skin is found in the 5th layer of 0.003721. So that the wing structure is declared safe according to the calculation of the Tsai-Hill criteria.
UAV V-SKY 14 NG aircraft for monitoring road traffic on the ITD Adisutjipto campus complex and its surroundings has special capabilities in taking off and landing vertically or VTOL. However, from the latest design that has been completed by previous researchers, the material on the wing of the UAV V-SKY 14 NG still uses styrofoam which is a low-strength material. Therefore, in this study, the authors wanted to analyze the wing of the V-SKY 14 NG UAV with several variations of the material used, as well as adding variations in skin thickness. The material used in this study is a sandwich composite material configuration. For getting a stronger and better wing configuration. The object of research in this final project is the wing of the V-SKY 14 NG UAV aircraft, to analyze the strength of the structure using ANSYS software with the stages of engineering data, geometry, model, composite assembly prepost, setup, solution, and result. The loading that is carried out is the take-off load on the VTOL rod, maneuver conditions and torque load with the support of the stringer, core and layer skin to be able to determine the stress value that occurs and the safety level of the structure. The maximum stress of the maneuver load on the wing configuration with a skin thickness of 1.38 mm in Epoxy Carbon Woven (230 GPa) Wet material with a fiber angle of 0?-90? is 4.5458 MPa. The failure criterion value for the maneuver load skin is found in the 5th layer of 0.003721. So that the wing structure is declared safe according to the calculation of the Tsai-Hill criteria.
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