Compact Methodology for Computing Limit-Cycle Oscillations in Aeroelasticity

A techniquefor computing limit-cycle oscillations of aeroelastic systems is presented. This techniquecan be used also for constructing and identifying reduced-order models that characterize accurately limit-cycle oscillations. The models presented use a spatial model reduction combined with a nonlinear identication technique. The finite difference in time method, a methodology similar to a finite element in time, is discussed. The specific novel aspects of the proposed method are noted. Numerical examples analyzing the dynamics of a panel forced by a buffeting aerodynamic load demonstrate the performance of the proposed methods.