ANALISIS NUMERIK KECEPATAN FLUTTER DENGAN
VARIASI TAPER RATIO, SUDUT SWEPT DAN ASPECT RATIO
PADA WING UAV CARGO-X
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Institusion
INSTITUT TEKNOLOGI DIRGANTARA ADISUTJIPTO
Author
EKO BAWONO, REZKY
Subject
T Technology (General)
Datestamp
2024-06-20 06:15:33
Abstract :
As the development of air transportation technology in this modern era, to much problem must be faced and solved by the engineers. The interaction between several scientific studies becomes a new problem that needs to be raised in an airplane. The interaction between structure and aerodynamics is worth considering in designing an airplane. The design of the aircraft must meet certain criteria to make the basis that must be specified in Design Requirement & Objectives by aircraft engineers or manufacturers. In the stage of conceptual design of an aircraft, it is very important to estimate the initial limits in predicting flutter in aircraft wings. Flutter is a symptom of dynamic instability due to the interaction between the elastic properties of the structure and aerodynamic forces. In this flutter phenomenon there is a transfer of energy from the air flow into the aircraft structure (in this case usually is the wing). The analysis process assumes that the wing is solid, then includes the type of material used in the analysis. The analysis process is carried out at a flying altitude of 200 m above sea level, assuming UAV fly with steady level flight. Several variations used in flutter speed analysis include variations in taper ratio, angle of attack, and aspect ratio on the wing. The modeling process uses the help of CATIA V5R20 software, the flutter speed analysis process using MSC Patran / Nastran software and FLDs 2012, and the graph making process of the velocity (m/s) - frequency (Hz) and speed (m/s) - damping (g) using Matlab 2016a software. Terms of the wing model are said to be safe if the damping value is less than 0.03. The results of the flutter speed test show that some variations affect the speed and slowness of objects flutter. The higher the taper ratio and aspect ratio, the smaller the flutter speed produced. Then, the effect of the swept angle is inversely proportional to the speed of flutter produced. The higher the value of the swept angle, the lower the speed of flutter wing.
As the development of air transportation technology in this modern era, to much problem must be faced and solved by the engineers. The interaction between several scientific studies becomes a new problem that needs to be raised in an airplane. The interaction between structure and aerodynamics is worth considering in designing an airplane. The design of the aircraft must meet certain criteria to make the basis that must be specified in Design Requirement & Objectives by aircraft engineers or manufacturers. In the stage of conceptual design of an aircraft, it is very important to estimate the initial limits in predicting flutter in aircraft wings. Flutter is a symptom of dynamic instability due to the interaction between the elastic properties of the structure and aerodynamic forces. In this flutter phenomenon there is a transfer of energy from the air flow into the aircraft structure (in this case usually is the wing). The analysis process assumes that the wing is solid, then includes the type of material used in the analysis. The analysis process is carried out at a flying altitude of 200 m above sea level, assuming UAV fly with steady level flight. Several variations used in flutter speed analysis include variations in taper ratio, angle of attack, and aspect ratio on the wing. The modeling process uses the help of CATIA V5R20 software, the flutter speed analysis process using MSC Patran / Nastran software and FLDs 2012, and the graph making process of the velocity (m/s) - frequency (Hz) and speed (m/s) - damping (g) using Matlab 2016a software. Terms of the wing model are said to be safe if the damping value is less than 0.03. The results of the flutter speed test show that some variations affect the speed and slowness of objects flutter. The higher the taper ratio and aspect ratio, the smaller the flutter speed produced. Then, the effect of the swept angle is inversely proportional to the speed of flutter produced. The higher the value of the swept angle, the lower the speed of flutter wing.
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