| Abstrakt: |
Objective: In this paper, the nonlinear flutter of the wing is investigated under the influence of aerodynamic control surfaces. Methods: The wing aerodynamic loads are determined using Peter's unsteady aerodynamic model, and the aerodynamic loads of the control surface are added with quasi-steady relations in the interior of the equations. The governing aeroelastic equations are presented in the structure of fully intrinsic and these equations are discretized using the finite difference method. Results: The effects of the presence of an aerodynamic control surface have been investigated based on the analytical-experimental relationships and considering the nonlinear effects of high control surface deflections. Furthermore, investigation of the effects of some important parameters such as deflections, location, chord size, and length of the control surface on the speed and frequency of flutter instability, is another achievement of this article. Conclusions: The results show that based on aeroelastic considerations, the deflection angle of the control surface has an important effect on the aeroelastic stability. Also, by bringing the control surface closer to the wing tip, increasing the thickness ratio and the chord ratio in accordance with other effective parameters, flutter suppression can be caused. [ABSTRACT FROM AUTHOR] |
Full text from SpringerLink