Flutter analysis of the panel treated with integrated and segmented constrained layer damping

In this study, the performance of viscoelastic constrained layer damping (CLD) in suppressing the flutter and vibration of panels is investigated with the special focus on the effects of three practically important features including the in-plane edge constraint, location of the CLD patch on the panel, and cutting the CLD patch. The panel is assumed to have infinite width and the higher-order shear deformation theory accounting for the through-the-thickness deformation is used for modeling the core. The finite element model is constructed using one-dimensional three-node elements with Lagrangian and Hermitian shape functions, and the piston theory is used for the aerodynamic pressure. Parametric studies are performed to determine the effects of in-plane constraints, partial CLD location, and segmeting the CLD. Results show that in-plain constraints can considerably affect flutter boundaries and also by adjusting the CLD location, the performance can be improved. However, the optimal location for maximum vibration damping would differ from the best location obtained for highest flutter suppression. Moreover it is found that the patch segmentation would not be beneficial for achieving better flutter suppression, while it would increase the damping of the structure.