MODIFIKASI UAV V-SKY 14 DAN ANALISIS KEKUATAN
STRUKTUR SAYAP, FUSELAGE, DAN TAIL UAV
V-SKY 14 NG MENGGUNAKAN SOFTWARE MSC
PATRAN/NASTRAN
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
EDI SAPUTRA, WAWAN
Subject
T Technology (General)
Datestamp
2024-06-21 06:09:19
Abstract :
Research and development of the Unmanned Aerial Vehicle (UAV) has been carried out by Adisutjipto College of Technology, Yogyakarta. One of the UAV that is currently being developed is the V-SKY 14 UAV with special vertical take-off and landing capabilities. On the results of the research strength UAV V-SKY 14, wing section analysis has been carried out under load Maneuver (Pull Up) and Vertical Take Off Landing (VTOL) conditions. However, there is one very critical load that has not yet been taken into this analysis, namely the torque load. This load occurs during the transition phase from vertical take off to cruising. At the aircraft function test stage, this load becomes a problem, so an additional structure is installed during manufacturing. In other hand, there are also obtained several technical problems, such as limited fuselage space, and the tail has a small Margin of Safety value due to aerodynamic loads. Because of this problem, the authors raised the discussion in the modification V-SKY 14 UAV and analysis of the structure strength V-SKY 14 NG UAV. The modeling process uses DS CATIA V5R21 software, calculation of structural strength using MSC Patran/Nastran 2012 software, and aerodynamic simulation using ANSYS R15.0 software. Loading on the UAV V-SKY 14 structure uses a 3.8 load factor based on Australia state UAV regulation (C.A.S.A. Australia Subpart C - Structure UA25.337). There are four loading cases, that is flying maneuver (pull up), Vertical Take Off Landing (VTOL), torque load, and aerodynamics load. After analyzed and obtained the value of the stress, then do the calculation to find out the Margin of Safety. After going through the structural strength analysis phase, the highest stress on the structure is obtained in a 15 degree pull up condition, precisely in the horizontal tail stringer with stress value 257 MPa and a Margin of Safety value 2,374. For the lowest Margin of Safety value is 0.376 with a stress value 0.466 MPa, it is in the horizontal tail core structure, conditioned by a torque load
Research and development of the Unmanned Aerial Vehicle (UAV) has been carried out by Adisutjipto College of Technology, Yogyakarta. One of the UAV that is currently being developed is the V-SKY 14 UAV with special vertical take-off and landing capabilities. On the results of the research strength UAV V-SKY 14, wing section analysis has been carried out under load Maneuver (Pull Up) and Vertical Take Off Landing (VTOL) conditions. However, there is one very critical load that has not yet been taken into this analysis, namely the torque load. This load occurs during the transition phase from vertical take off to cruising. At the aircraft function test stage, this load becomes a problem, so an additional structure is installed during manufacturing. In other hand, there are also obtained several technical problems, such as limited fuselage space, and the tail has a small Margin of Safety value due to aerodynamic loads. Because of this problem, the authors raised the discussion in the modification V-SKY 14 UAV and analysis of the structure strength V-SKY 14 NG UAV. The modeling process uses DS CATIA V5R21 software, calculation of structural strength using MSC Patran/Nastran 2012 software, and aerodynamic simulation using ANSYS R15.0 software. Loading on the UAV V-SKY 14 structure uses a 3.8 load factor based on Australia state UAV regulation (C.A.S.A. Australia Subpart C - Structure UA25.337). There are four loading cases, that is flying maneuver (pull up), Vertical Take Off Landing (VTOL), torque load, and aerodynamics load. After analyzed and obtained the value of the stress, then do the calculation to find out the Margin of Safety. After going through the structural strength analysis phase, the highest stress on the structure is obtained in a 15 degree pull up condition, precisely in the horizontal tail stringer with stress value 257 MPa and a Margin of Safety value 2,374. For the lowest Margin of Safety value is 0.376 with a stress value 0.466 MPa, it is in the horizontal tail core structure, conditioned by a torque load
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