Analyzing and predicting the nonlinear aeroelastic response

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Aging aircraft or operational aircraft carrying heavy externals may exhibit nonlinear aeroelastic phenomena, such as limit cycle oscillations (LCO), within their flight envelope. Generally the LCO has a negative effect on the aircraft performance, but limited amplitude LCOs due to non-linearities, are a better alternative than the onset of destructive flutter oscillations. Thus, for the flight vehicle design, and in the study of active and adaptive control, it is important to detect the presence of the non-linearities. Moreover, finding the particular type of the non-linearities is also important. The main objective of this project is to develop methods for detecting the nonlinearities associated with an aeroelastic system, and to predict the aeroelastic response for changing flight conditions. The proposed methodology incorporates mathematical analysis and statistical methods. Using only a set of transient data, these methods are capable of identifying nonlinearities and determining the asymptotic state of the aeroelastic system. Oscillations similar with the aeroelastic response can be found as the output of many other nonlinear dynamical systems. Thus, the present project has a strong potential not only in the study of nonlinear aeroelasticity, but also in the analysis of the nature of nonlinearities and in the prediction of financial or biomedical complex data.