GEOMETRI SIZING DAN PEMODELAN 3D PESAWAT
FIXED WING UAV AE-01 UNTUK MISI PEMANTAUAN DAN
PEMOTRETAN LAHAN PEMBANGUNAN
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
Satria Nanditaputra, Daniel
Subject
T Technology (General)
Datestamp
2024-02-27 03:14:11
Abstract :
Unmanned Aerial Vehicle (UAV) is a system with the characteristics of a flying vehicle that can be controlled remotely. Given the vast territory in Indonesia, this technology is needed that is able to obtain effective and efficient Monitoring and Aerial Photography. Therefore, the role of UAV aircraft is needed which has advantages in the value of its work effectiveness. The research method used is a literature study method, with several sources from theory books and research journals regarding the design and design of valid aircraft. The initial stage in this design process is to approach the design through linear regression, determination of Avionic components, and determination of aircraft geometry in accordance with predetermined criteria, then 3D modeling will be carried out using CATIA V5 Software. The results of the regression approach and geometry calculation, the aircraft has a Fuselage length of 1,224 m, Wing Span 1,75 m, Weight 1,99 Kg, V Stall 7,341 m/s, Wing Loading 41,589 N/m , Wing Area 0,469 m , Moment Tail Arm 0,6732 m, Horizontal Tail Area 0.093 m , Vertical Tail Area 0.048 m.
Unmanned Aerial Vehicle (UAV) is a system with the characteristics of a flying vehicle that can be controlled remotely. Given the vast territory in Indonesia, this technology is needed that is able to obtain effective and efficient Monitoring and Aerial Photography. Therefore, the role of UAV aircraft is needed which has advantages in the value of its work effectiveness. The research method used is a literature study method, with several sources from theory books and research journals regarding the design and design of valid aircraft. The initial stage in this design process is to approach the design through linear regression, determination of Avionic components, and determination of aircraft geometry in accordance with predetermined criteria, then 3D modeling will be carried out using CATIA V5 Software. The results of the regression approach and geometry calculation, the aircraft has a Fuselage length of 1,224 m, Wing Span 1,75 m, Weight 1,99 Kg, V Stall 7,341 m/s, Wing Loading 41,589 N/m , Wing Area 0,469 m , Moment Tail Arm 0,6732 m, Horizontal Tail Area 0.093 m , Vertical Tail Area 0.048 m.
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