Flutter Instability Analysis of a Aircraft Morphing Wing in spanwise direction affected by various parameters

In this paper, the flutter instability of a morphing wing with change in its length is investigated. Presence of a morphing part in the wing makes a difference in the whole aeroelastic equations. In this regrad, Euler-Bernoulli beam model is considered to simulate the structural behavior of the wing and the well-known Peters unsteady aerodynamic model is utilized to compute the aerodynamic loads. The obtained partial differential aeroelastic equations are translated to the ODE ones using Galerkin’s method. Then, the eigenvalue approach is utilized to study the flutter instability of the aeroelastic system. The novelty of this work is to study the simultaneous effects of some parameters such as engine locations, thrust, sweep angles on the flutter instability of the morphing wing. The obtained results are compared with those available in the literature, and a good agreement is observed. It is found that the presence of engine or a low sweep angle simultaneously with the change of the morphing wing span decrease the flutter speed and a faster morphing process can get better aeroelastic performance.