Daniel, Tilahun (PhD)Fasil, Erkyhun2022-03-262023-11-182022-03-262023-11-182022-03http://etd.aau.edu.et/handle/12345678/30905In this research, an Unmanned Aerial Vehicle (UAV) wing made of carbon epoxy composite material was used to investigate the wing static structural and modal response. The aerodynamic pressure load was calculated on ANSYS fluent by taking into account practical operational conditions. Two parametric studies were conducted where the first study had three models by varying the wing front and rear spar locations. The location of the front spar of model 1, model 2, and model 3 was at 18%, 22%, and 25%, whereas the rear spar was located at 62%, 65%, and 65%, respectively. On the other hand, the second parametric study had five different composite ply orientations of the wing skin, including [0/30/0/30/0], [0/45/0/45/0], [0/60/0/60/0], [0/90/0/90/0], and [-45/45/-45/45/-45]. Results from static structural analysis of varying spar locations showed that deformation has a maximum value at model 3 whereas bending and shear stress were maximum at model 2. On the other hand, deformation, bending, equivalent, and shear stress was minimum at model 1. The result from varying composite ply orientations showed that maximum and minimum deformation occurs at [0/30/0/30/0] and [0/90/0/90/0] ply orientations, respectively. The shear stress value was maximum at [-45/45/-45/45/-45]; Meanwhile, bending and equivalent stress were maximum at [0/30/0/30/0], while all stresses were minimum at [0/90/0/90/0]. From the modal analysis result, varying the spar location shows less effect on the natural frequency of the wing. Moreover, it was observed that model 1 had better structural performance than the other two models. On the other hand, the natural frequency of the first mode was maximum at [0/90/0/90/0] and minimum at [0/30/0/30/0], while in the last mode, the maximum and minimum values occur at [0/30/0/30/0] and [0/90/0/90/0], respectively. In General, the study showed that when the wing front and rear spar are close to each other and when [0/90/0/90/0], wing skin ply orientation applied, the wing had a better structural performance.en-USStatic StructuralModalUAVComposite WingThesis