In this study the procedures of structural analysis of a typical transport aircraft wing has been followed. The wing model has been drawn using CATIA® V5; this model consists of several structural components such as spars, ribs and skin. The model has been exported into structural analysis software ANSYS® 2016. Stresses, strains, deformations and safety factors were obtained for the model. It is found that the obtained stresses caused by the aerodynamic loads on the wing are within the design structural limits where the failure by yield or buckling has not been occurred

The aim of this paper is to determine and study the aerodynamics characteristics of an Agricultural Spraying Unmanned Air Vehicle (ASUAV) that designed in the Faculty of Engineering-Omdurman Islamic University. Since flight testing can be expensive and dangerous, other methods are required to simulate flight test conditions for low subsonic vehicle system. In this research, Computational Fluids Dynamics (CFD) was used to simulate the flight test and determine the aerodynamic characteristics such as lift and drag coefficients at various angles of attack. The quality of flow pattern around the ASUAV was clearly observed. Generally, the current approach shows that the proposed configuration has suitable aerodynamic characteristics. The promising results of this study opened the door for developing and manufacturing the ASUAV which have been successfully flight in June 2012.

The wing of an UAV plays an important role in the vehicle behavior. In order to understand its main influences, a dedicated test rig was designed and realized to load the composite wing in the bending configuration. This study describes the details of a numerical and an experimental investigation done with the aim to identify the stiffness characteristics of a composite wing structure of an Unmanned Aerial Vehicle (UAV). The wing was divided into discrete span-wise stations. Wooden bolted clamps were placed along the upper and lower surfaces of the wing at each station, to support the applied load and the displacement transducers. The wing was suspended and secured horizontally (at the wingfuselage connection base) in a rigid test stand in an orientation similar to the familiar cantilever beam. A single weight was applied individually, at each station to stress the wing in elastic yield, as in real conditions. Displacement transducers were installed to measure the vertical displacements of the entire wing, and monitor any motion of the overall airframe. During the measurement procedures (loading and unloading) were conducted on the specified stations, and repeated 10 times, the mean value of the measurements was obtained. A detailed numerical model of the composite wing was developed using of the finite element method in order to reproduce the experimental experiences. Numerical and experimental results were compared to validate the model of the composite wing. All the obtained parameters are mainly being used in a development process of UAV behavior.

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