PERANCANGAN PESAWAT UAV SOLAR CELL
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
WAYAN SUKMA BAYU GUMILANG ADI PUTRA, I
Subject
T Technology (General)
Datestamp
2024-05-06 08:58:11
Abstract :
UAV (Unmanned Aerial Vehicle) is an aircraft that flies without a pilot accompanying the aircraft during the flight. UAVs are used in surveillance or monitoring where the UAV is given a camera to record an object which is used as monitoring data. To respond to traffic conditions and conditions in the middle of the city, a UAV is needed that can fly vertically and can move quickly to reach traffic conditions in different places and can also carry out shooting missions. The methods used for this design are analytical methods and numerical methods with reference to Raymer and Roskam's books. Design begins by determining DR&O, determining weight, wing span, wing geometry, fuselage and tail. The results of the geometry are drawn in 3 dimensional form using CATIA software, then the 3 dimensional results are analyzed to determine the aerodynamic characteristics of the UAV using ANSYS software. From the design results, the UAV Solar Cell configuration and geometry are obtained with the following specifications: Aircraft configuration Components Wing configuration Sweepback wing Tail, Power plant Thurust Airfoil Wing (NACA 0012,0018,0024,0030) as a result of aerodynamic analysis carried out on the results of the UAV solar cell design with a speed of 20m/s and a height of 150 meters above sea level, at an angle of attack of 0o the CL is obtained at 0 .0259253 and CLmax of 0.413903 at an angle of 21o. The value of CD at an angle of attack of 0o is 0.030259 and CDmax is 0.138968 at an angle of 21o
UAV (Unmanned Aerial Vehicle) is an aircraft that flies without a pilot accompanying the aircraft during the flight. UAVs are used in surveillance or monitoring where the UAV is given a camera to record an object which is used as monitoring data. To respond to traffic conditions and conditions in the middle of the city, a UAV is needed that can fly vertically and can move quickly to reach traffic conditions in different places and can also carry out shooting missions. The methods used for this design are analytical methods and numerical methods with reference to Raymer and Roskam's books. Design begins by determining DR&O, determining weight, wing span, wing geometry, fuselage and tail. The results of the geometry are drawn in 3 dimensional form using CATIA software, then the 3 dimensional results are analyzed to determine the aerodynamic characteristics of the UAV using ANSYS software. From the design results, the UAV Solar Cell configuration and geometry are obtained with the following specifications: Aircraft configuration Components Wing configuration Sweepback wing Tail, Power plant Thurust Airfoil Wing (NACA 0012,0018,0024,0030) as a result of aerodynamic analysis carried out on the results of the UAV solar cell design with a speed of 20m/s and a height of 150 meters above sea level, at an angle of attack of 0o the CL is obtained at 0 .0259253 and CLmax of 0.413903 at an angle of 21o. The value of CD at an angle of attack of 0o is 0.030259 and CDmax is 0.138968 at an angle of 21o
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