Abstract
In this study, we analyze the flutter, limit cycle oscillation, and different nonlinear oscillations of rectangular panels with an all-over part-through crack. We perform these analyses for panels according to the first order shear deformation or Mindlin plate theory. We accurately study the effects of the depths and locations of cracks on various aeroelastic characteristics of moderately thick rectangular panels. These analyses show that the amplitudes of nonlinear vibrations are increased for cracks at many depths and locations. However, the panel has lower amplitude vibrations relative to its intact counterpart for cracks in some locations. Changing the location and depth of the crack obtains different maximum limit cycle oscillation amplitudes compared with the intact counterpart. The cracked panel may also exhibit complex oscillations in addition to the limit cycle oscillation of the intact panel. These analyses show that cracks have significant effects on the flutter boundary and the amplitude of the limit cycle oscillation.
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