Aeroelastic model of typical section with control surface freeplay

Abstract

The aeroelasticity studies the mutual interaction between aerodynamic and structural effects. It is known that this relationship has often nonlinear responses, causing various problems such as flutter, limit cycle oscillations and other phenomena difficult to diagnose. So it is vital the development of studies in this area for increase the security of aircrafts and also new technology projects to stop or minimize these effects, such as the development of smart structures. In the case of aeroelasticity, mathematical models for numerical solution are formed by the coupling of specific models for behavior dynamic-structural and for the behavior of aerodynamics non-stationary. This work aims to develop a computer program to study the nonlinear effects caused by a freeplay in a command surface of a typical section under non-stationary. For this will be produced a mathematical model based on the vortex lattice method non-stationary attached to the structural model of three degrees of freedom, ie, flexion / rotation on the wing and control surface deflection. Will be possible to solve the system of structural equations based on the aerodynamic loading resulting from the program. Experimental tests will be performed in a wing following the mathematical model, aiming at a better learning of these real aeroelastic effects and subsequent validation of the mathematical model. (AU)