Abstract
The effectiveness of piezoelectric actuators in reducing vibratory response due to buffet loads on the F-16 ventral fin was investigated numerically. The study was initiated by tuning a finite element model of the ventral fin to existing ground vibration test data. Strain energy profiles were determined for the first five mode shapes. The modes most critical for active control were determined through a flutter analysis, in conjunction with existing flight test data, as well as a review of the structural detail of previous fin failures. Piezoelectric actuator patches were located within the regions of highest strain energy and aligned with the principal strain vectors in those regions.
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