چكيده به لاتين
Aeroelastisity is one of the main reasons for the occurance of a variety of aircraft instability, so consideration of its effect on the design of the aircraft structure is necessary. Among these instabilities, which is great importance, is the phenomenon of fluctuation with a high frequency, or flutter. The use of advanced design concepts that contribute to the improvement of the static and dynamic response quality of the aircraft has always been one of the goals of designers of air structions, one of the ways to achieve such goals is the use of composite materials in structures.
In this study, the behavior of the aeroelastic composite wing in the compressible flow is investigated. In order to simulate the behavior of the wing structure, a beam made of anisotropic materials having a thin-walled cross section and, the circumferentially asymmetric stiffness (CAS) configuration method has been used. In order to obtain the best configuration for the purpose of having a higher flutter speed, the four configuration samples [θ]_6 , [θ/-θ]_3 , [θ_3/-θ_3 ] and [0_2/θ/-θ/0_2 ] in the 0-90 degrees were compared with each other, this comparison was done for two modes in the shearable and unshearable beam configuration in equations. In the analyses carried out in this section, it was observed that at angles between 60 and 90 degrees, there were significant changes in the results of flutter velocities, including a sudden increase in flutter speed at an angle 70 degree, with the removal of the transverse shear stress effect. Although including foam in the structure between composite skin layers resulted in improved stability characteristics, however selection of a suitable geometrical model which is by increase the cross sectional area of the beam and maintain its wall thickness would incredibly affect the obtained results.
