The flutter boundary prediction of a wing based on the nonstationary data measurement is proposed. System dynamics is represented by an ARMA model, whose coefficients are estiamted in each sampling instance using the RPE method. The stability margin of the aeroelastic system is evaluated by the Jury's stability parameter that is calculated from the AR part of the estimated coefficients. To examine t he performance of the estimation, a numerical simulation using a simple bending-torsion wing is conducted, in which the flow speed is increased at a constant rate. The flutter boundary is predicted by extrapolating the quadratic curve fitted to the flight speed. The result shows that the present method can use the data observed in a wide range of velocities to predict the flutter boundary and give an accurate prediction, while the conventional damping method can be applied only to the data near flutter boundary.
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