ANALISIS BUCKLING STRUKTUR WING TUAV AEROSTAR DENGAN MATERIAL KOMPOSIT CARBON FIBRE REINFORCE POLYMER MENGGUNAKAN METODE ELEMEN HINGGA

Abstrak

ABSTRACT

Unmanned Aerial Vehicle (UAV) is an unmanned aircraft that is remotely controlled from a station or control center via radio frequency or automatically by computer. The Research and Development Service (Dislitbang) of the Air Force is currently conducting research on the Aerostar UAV called the Tactical Unmanned Aerial Vehicle (TUAV). The geometry of the wing consists of skins, ribs and spars using carbon fiber reinforce polymer composite material . Wing aerodynamic loads in the form of lift are distributed eleptically along the wing span and evenly along the chord. Static analysis cannot be considered safe because there are other factors that can cause failure in aircraft structures, namely structural instability (buckling). The material used in the wing structure is composite with 5 cases of lamina arrangement. The boundary conditions applied are fixed at the root and free at the wing tip. The problem raised in this research is how the lamina arrangement affects the response of the aircraft wing structure. The finite element method is used for buckling analysis to solve this problem. The calculation results show that 4 cases of lamina arrangement fail 1 case is safe with buckling factor 1.94.

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Keyword: UAV, Buckling Analysis, Composite, Wing, Finite Element Method..