PARAMETRIC STUDY ON TACTICAL UNMANNED AERIAL VEHICLES (TUAV) WINGS BASED ON AEROELASTIC PERFORMANCE

• Main Author: Gede Anjastara Bandem, I
• Format: Final Project
• Language: Indonesia
• Subjects: Teknik (Rekayasa, enjinering dan kegiatan berkaitan)
• Online Access: https://digilib.itb.ac.id/gdl/view/81217
• Institution: Institut Teknologi Bandung

<p align="justify">The fairly rapid development of Unmanned Aerial Vehicles (UAV) occurs because of the high potential for use of UAVs today. UAVs can be used in various missions such as cargo delivery, aerial reconnaissance, weather observation, and other military purposes that can reduce the risk of human safety on dangerous missions. Flutter is a phenomenon of instability in structures due to the interaction of inertial, elasticity and aerodynamic forces. As part of the aeroelastic analysis, there is verification of the flutter limit results of the flying vehicle, the structural response in the form of deflection on the wings has been evaluated at several flight speeds that being given a gust load. In this final project, an analysis was carried out using the finite element method with MSc Nastran software to determine the structural dynamics of the METU TUAV wing structure such as vibration mode and natural frequency. Then an aeroelastic instability analysis was carried out to determine whether there was an indication of a flutter phenomenon. From the results of the analysis, there are indications of a divergence phenomenon at a flight speed of 230 m/s which can be seen on the U-f graph, when the 1st bending mode curve goes towards zero. When a gust load is applied at a flight speed of 230 m/s, a high deflection occurs and is not followed by oscillation afterwards, showing that structure is unstable.<p align="justify">