PEMODELAN DAN ANALISIS AEROELASTIK PADA SAYAP TACTICAL UNMANNED AERIAL VEHICLES (TUAV)

• Main Author: Wahyanto, Willy
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/62007
• Institution: Institut Teknologi Bandung

Tactical Unmanned Aerial Vehicles (TUAV) are drones that have a mission to assist tactical commanders. TUAV must be made in order for the aircraft to be safe and airworthy. One of the phenomena of structural failure that can occur is due to aeroelastic instability through the interaction between forces of inertia, elasticity, and aerodynamics. This study aims to reconstruct and analyze the aeroelastic dynamic characteristics of the TUAV wing structure that has been developed by previous researchers. The aircraft has the complexity of the material side where most of the wing structure is made of composites which are anisotropic materials with characteristics depending on the definition of material properties such as ply count and fiber direction. This provides different structural characteristics with isotropic material structure characteristics so that in this study three-dimensional (3D) modeling was used so that the complexity of the structure and composite material can be well represented. The reconstruction of the TUAV wing model with a complete boundary condition called model A was validated by the structural dynamics in the study that was referred to. It is known that model A has the same type of mode shape and the error relative in natural frequency is below 10%. The model that is the most representative of the reference data is model C that has been done structural modifications. Analysis with boundary conditions simplified as cantilevers have an error relative of under 5% in the first to sixth mode shape so it is concluded that simple boundary conditions have little effect on the structural dynamics characteristics at low-mode. Furthermore, dynamic aeroelasticity analysis was reviewed from 10 m/s to 320 m/s using commercial software based on the finite element method. In the previous study, predicted divergence speed value using a simple 2D torsional analysis of 263 m/s. Whereas in this study, for models with complete boundary conditions, there was no indication of aeroelastic instability. But for models with simple boundary conditions, an indication of the divergence phenomenon is obtained at a speed of 300 m/s.