ANALISIS KARAKTERISTIK AEROELASTISITAS DINAMIK SAYAP PESAWAT TEMPUR DENGAN STRUKTUR KOMPOSIT SECARA KOMPUTASIONAL

• Main Author: Untarsa, Yohanes
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/66869
• Institution: Institut Teknologi Bandung

-Fighter aircraft are designed to operate in extreme conditions, i.e., highspeed regimes. One limitation in terms of the flight speed is based on the aeroelastic characteristic, i.e., the critical flutter speed. Furthermore, with composite materials on the main structural components of a fighter aircraft, optimized composite configurations, i.e., layers (plies) thicknesses and orientations, need to be assessed. The present work focuses on the dynamic aeroelasticity analyses of a composite fighter wing by means of the finite element method coupled with unsteady aerodynamic models. The wing's dynamic instability, i.e., flutter characteristic, is concerned. A sensitivity study is conducted to evaluate the changes in the critical flutter speed concerning the composites’ plies thicknesses. Based on the aeroelastic analysis, there is no sign of flutter in the subsonic regime. However, there is an indication of flutter in the hypersonic region at a critical speed of 2340 m/s. This critical speed value is way beyond the maximum operating limit of the aircraft (Mach 1.82). Thus, a sensitivity analysis is done to investigate the possibility of further optimizing the structure concerning its critical flutter speed. The results indicated that the component with the highest sensitivity is the section near the root area. The natural frequencies and the critical speed are increased with the thickness. For twice the original thickness, the critical flutter speed increases to 2478 m/s. In contrast, half the thickness changes the critical flutter speed to 2022 m/s. Hence, it is possible to optimize the structure further to optimize the decrease composite thickness and the structural weight.