Abstract
This research paper presents the dynamic and aeroelastic analysis of functionally graded carbon nanotube reinforced (FG-CNTRC) laminated composite plates with damage in the subsonic regime. First order shear deformation theory (FSDT) is applied to develop finite element code in MATLAB environment for structural analysis. The anisotropic damage formulation based on the concept of stiffness reduction is introduced into the finite element formulation to include the damage in the plate. To implement aeroelastic analysis through PK-method, the required aerodynamic force matrix coefficients, are generated in MSC.Nastran by supplying modal parameters (obtained from structural analysis) through direct matrix abstract program (DMAP) using doublet-lattice-method (DLM). The accuracy of the present model has been analyzed by tackling the various numerical illustrations and validated with some of earlier published literature. Further, the effect of various parameters like CNT fiber volume fraction, lamination sequence, damage location and orientation on flutter characteristic are studied.
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