This paper concentrated about the effect of both the pseudorandom or random vibration (wind waves) and aerodynamic forces on the wing of unmanned aerial vehicle, which brought the attention of specialists in this field during last years, the performance of wing is improved on a definitive solution for the vibration problems which cause failure in the wings of UAV. The distribution of stresses and distortions with aerodynamic loads is studied. Factors such as tension, pressure and shear stress showed on wing of UAVs due to vibration which caused the structure of wing to break down and then failure. The experimental study was carried out by using wing made of composite material (foam and cover by lamination plate), where airfoil type (NACA Clark y) installed inside wind tunnel of low velocity. It is found that the vibration acceleration at constant wind velocity with variation of attack angle of the wing, it is obtained the relationship between the acceleration and the frequency using the LABVEIW program which analyzed and identified the distribution of forces on the wing. The stress concentration areas is created and found under failure occurs, the aerodynamic force, torsion torque and magnitude of deformation is calculated. It is concluded that the close areas from the root wing (fixed end) is most likely to collapse or break.

This paper includes an experimental study of the effect of irregular vibrations (random vibration) resulting from dynamic aerodynamic load or the turbulent winds of the unmanned aerial vehicle (UAV) wing, as well as finding aerodynamic forces affecting the wing. The objective of this study is to determine the concentration areas of the force in which the failure occurs and to know the behavior of random vibration and its effect on the wing structure. The wing was constructed and manufactured with suitable dimensions and then the wing was installed inside the wind tunnel of the test. The wing has been tested at five angles of attack (0º, 5º, 10º, 15º and 20º) and certain wind velocities. Through the sensors and associated signal analyzers, the relationship was obtained between acceleration and frequency acceleration of specific points on the wing surface and the forces of drag, lift and torque were calculated. The results show, it was found that the greatest value of the forces is concentrated in the area near the edge fixed at the wing root especially in the large attack angles. Also it was concluded that the drag and lift forces and torque torsional wing increases proportional to the increase in wind velocity and angle of attack