Aeroelastic Damping Model Derived from Discrete Euler Equations

摘要

The prediction of flutter onset based dn aerodynamic modeling using computational fluid dynamics can be made using an augmented system of equations. Computational times similar to those required for computational fluid dynamics steady-state calculations have been reported for wing test cases. However, for such methods to be fully useful, information about damping must be obtainable without reverting to full-order time-domain simulation. This paper presents a method for computing damping based on a reduced-order modeling approach that systematically derives a two-degrees-of-freedom model from the full discrete system of equations. The method is based on a change of variables that employs the critical eigenvector of the aeroelastic system. The ability of this model to predict the damping for a model problem and for two wing test cases is shown.