RANCANG BANGUN SAYAP PESAWAT UAV FLYING WING UNTUK
MISI PEMANTAUAN GUNUNG MERAPI
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
ANTONIO DOS SANTOS, DAVID
Subject
T Technology (General)
Datestamp
2024-06-27 07:20:59
Abstract :
A wing is an important part of the airplane because it has a function as a producer of lift to be able to lift airplanes on the air. This research aimed to design and build a special wing for UAV with the flying Wing type. The writer used design data and requirements that have been identified by previous research as the purpose of the airplane for monitoring Mount Merapi and the writer also used comparative airplane data as an assumption to determine wing span. This study only calculated the initial dimensions of the wing, namely wing span, wing area, wing loading, aspect ratio, chord tip, and elevon span. After doing the calculation, it moved to the modeling process for the purposes of analysis with CFD and FEA ansys software to identify the maximum stress on the frame and its deflection. After calculating the wing span design, the data obtained were wing span of 1.99 m, wing area of 0.573 m2 , wing loading of 35.281 N/m2 , aspect ratio of 6.9, chord tip of 0.09 m, and elevon span of 0.975 m. From the results of the analysis, a maximum stress of 2.6782 MPa was obtained in the root spar section and deflection occurred in the tip section of 0.00285 m. Furthermore, wings were produced and assembled on airplane and the airplane can fly well with MTOW 3 Kg
A wing is an important part of the airplane because it has a function as a producer of lift to be able to lift airplanes on the air. This research aimed to design and build a special wing for UAV with the flying Wing type. The writer used design data and requirements that have been identified by previous research as the purpose of the airplane for monitoring Mount Merapi and the writer also used comparative airplane data as an assumption to determine wing span. This study only calculated the initial dimensions of the wing, namely wing span, wing area, wing loading, aspect ratio, chord tip, and elevon span. After doing the calculation, it moved to the modeling process for the purposes of analysis with CFD and FEA ansys software to identify the maximum stress on the frame and its deflection. After calculating the wing span design, the data obtained were wing span of 1.99 m, wing area of 0.573 m2 , wing loading of 35.281 N/m2 , aspect ratio of 6.9, chord tip of 0.09 m, and elevon span of 0.975 m. From the results of the analysis, a maximum stress of 2.6782 MPa was obtained in the root spar section and deflection occurred in the tip section of 0.00285 m. Furthermore, wings were produced and assembled on airplane and the airplane can fly well with MTOW 3 Kg
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