Two methods are presented for flutter testing during an aircraft flight. Proposed procedures are based on time signal windowing and recursive identification method. The signal segmentation algorithm gives smoother results but delayed on time depends on time window and overlapping size. This method can be applied to on-line identification in non-time critical system. The estimation based on recursive identification algorithm gives damping ratio quicker but results strongly depends on algorithm parameters, mainly forgetting factor. The recursive identification method can be useful for practical flutter estimation after very careful algorithm parameters adjustment. The simulation results of proposed procedures are discussed for two degrees of freedom system with varying damping. The methods have been applied to identify the flutter region for trainer jet directly from flight vibration measurements. The flutter was detected on the left and right aft stabilator.
Real-time modal analysis and its application for flutter testing
Echtzeit-Modalanalyse und deren Anwendung für den Test der Flatterschwingung
2004
6 Seiten, 14 Bilder, 11 Quellen
Aufsatz (Konferenz)
Englisch
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