DESAIN DAN ANALISIS AERODINAMIKA
AEROMODEL FIXED WING VTOL UAV DENGAN MISI
PEMANTAUAN KOTA YOGYAKARTA
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
DOUTEL SARMENTO VONG, SIMPLICIO
Subject
T Technology (General)
Datestamp
2024-04-05 03:27:49
Abstract :
UAV or unmanned aerial vehicles can be controlled remotely. The utilization of UAV as a monitoring medium has an advantage in working. This technology can be a replacement for satellites observation which also has a fairly high cost in operation. Therefore, this research discussed the initial design of unmanned aircraft that has a special mission to observe urban areas in Yogyakarta. The research focuses on discussing the process of designing unmanned flying wing aircraft with the addition of VTOL systems. The designed aircraft was operated at an altitude of 150 meters above sea level with a cruising speed of 19.4 m/s. The process of 3-dimensional model designing used Solidworks software and simulated airflow testing on the design. The result of the design of the VTOL flying wing UAV aircraft was a fuselage length of 0.985 meters, a wingspan of 3 meters and an aircraft weight of 11.3108 kg. From aerodynamic analysis on the VTOL UAV Fixed Wing Aeromodel design at a speed of 19.5 m/s and 150 meters above sea level, at an attack angle of 0o obtained CL of 0.129 and Clmax of 0.363 at an angle of 4o. The value of the CD at the attack angle of 0o was 0.113 and CDmax was 0.199 at the angle of 4o. The results of the analysis showed that the design aircraft could be airworthy.
UAV or unmanned aerial vehicles can be controlled remotely. The utilization of UAV as a monitoring medium has an advantage in working. This technology can be a replacement for satellites observation which also has a fairly high cost in operation. Therefore, this research discussed the initial design of unmanned aircraft that has a special mission to observe urban areas in Yogyakarta. The research focuses on discussing the process of designing unmanned flying wing aircraft with the addition of VTOL systems. The designed aircraft was operated at an altitude of 150 meters above sea level with a cruising speed of 19.4 m/s. The process of 3-dimensional model designing used Solidworks software and simulated airflow testing on the design. The result of the design of the VTOL flying wing UAV aircraft was a fuselage length of 0.985 meters, a wingspan of 3 meters and an aircraft weight of 11.3108 kg. From aerodynamic analysis on the VTOL UAV Fixed Wing Aeromodel design at a speed of 19.5 m/s and 150 meters above sea level, at an attack angle of 0o obtained CL of 0.129 and Clmax of 0.363 at an angle of 4o. The value of the CD at the attack angle of 0o was 0.113 and CDmax was 0.199 at the angle of 4o. The results of the analysis showed that the design aircraft could be airworthy.
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