ANALISIS STRUKTUR WING UAV-C21 (KARGO)
MENGGUNAKAN PENDEKATAN NUMERIK
DENGAN METODE ELEMEN HINGGA
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
FITRIAN AL HADI, PANDY
Subject
T Technology (General)
Datestamp
2024-05-06 02:42:21
Abstract :
UAV-C21 (cargo) is a type of unmanned aircraft that has the mission of delivering goods which later this aircraft will carry logistics for disaster victims in disaster-prone areas. Cause in previous research, internal design modeling and analysis of the strength of the wing structure had not been carried out. So that in this research will be carried out to determine the internal design modeling and analysis of the strength of the wing structure. This is an advanced stage in the design of an aircraft or UAV, so that the analysis of the strength of the wing structure needs to be taken into account to determine the correct structural and material configuration so that when used the aircraft is able to withstand the loads received. The wing modeling process uses CATIA software, then the wing structure analysis process using software CFD, with stages of engineering data, geometry, model, ansys composite prepost, setup, solution, and result. The loading carried out is the take-off load on VTOL rod, maneuver conditions and limit negative loads with support on the spar. After going through the stages of this research, it was found that the UAV-C21 (cargo) has a wing configuration with skin (2,08 mm), 6 ribs (5,2 mm), 2 spars (7,8 mm), and VTOL rods (3,12 mm) The maximum stress value that occurs in the wing structure as a whole is located on the lower surface skin in contact with VTOL rod, compressive stress of 126,37 MPa and tensile stress of 77,87 MPa at load factor 3,8 and a maximum total displacement on the wing tip against value 63,253 mm at load factor 3,8. The maximum value of the wing failure criteria is located on the first lower surface skin layer in contact with VTOL rod against value of 0,4738 at load factor 3,8, so that the wing structure is declared safe according to Tsai-Hill calculations.
UAV-C21 (cargo) is a type of unmanned aircraft that has the mission of delivering goods which later this aircraft will carry logistics for disaster victims in disaster-prone areas. Cause in previous research, internal design modeling and analysis of the strength of the wing structure had not been carried out. So that in this research will be carried out to determine the internal design modeling and analysis of the strength of the wing structure. This is an advanced stage in the design of an aircraft or UAV, so that the analysis of the strength of the wing structure needs to be taken into account to determine the correct structural and material configuration so that when used the aircraft is able to withstand the loads received. The wing modeling process uses CATIA software, then the wing structure analysis process using software CFD, with stages of engineering data, geometry, model, ansys composite prepost, setup, solution, and result. The loading carried out is the take-off load on VTOL rod, maneuver conditions and limit negative loads with support on the spar. After going through the stages of this research, it was found that the UAV-C21 (cargo) has a wing configuration with skin (2,08 mm), 6 ribs (5,2 mm), 2 spars (7,8 mm), and VTOL rods (3,12 mm) The maximum stress value that occurs in the wing structure as a whole is located on the lower surface skin in contact with VTOL rod, compressive stress of 126,37 MPa and tensile stress of 77,87 MPa at load factor 3,8 and a maximum total displacement on the wing tip against value 63,253 mm at load factor 3,8. The maximum value of the wing failure criteria is located on the first lower surface skin layer in contact with VTOL rod against value of 0,4738 at load factor 3,8, so that the wing structure is declared safe according to Tsai-Hill calculations.
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