Modal identification results are presented that were obtained from recent flight flutter tests of a drone vehicle with a research wing equipped with an active flutter suppression system (FSS). Frequency and damping of several modes are determined by a time domain modal analysis of the impulse response function obtained by Fourier transformations of data from fast swept sine wave excitation by the FSS control surfaces on the wing. Flutter points are determined for two different altitudes with the FSS off. Data are given for near the flutter boundary with the FSS on.
Application of a flight test and data analysis technique to flutter of a drone aircraft
Conference on Structures, Structural Dynamics and Materials ; 1981 ; Atlanta, GA
1981-01-01
Miscellaneous
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English