Abstract
The frequency domain method and the time domain method based on modal superposition method of flutter analysis are not applicable when dealing with the aeroelastic problems (thermoaeroelasticity, etc.) in which the structural vibration characteristics (natural vibration) change with time. To solve this problem, this paper introduces the finite element direct integration method into the aeroelastic analysis. The flutter critical velocity of a wing plate model under subsonic conditions is obtained using this method and the comparison of the two methods is completed. The result shows the applicability of the direct integration method in the aeroelastic analysis of aircraft, which is the foundation of further research on aeroelastic problems with time-varying structural natural vibration.
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