Nonlinear flutter of composite laminates with curvilinear fibres using a full linearized aerodynamic theory

This paper studies nonlinear flutter of rectangular variable stiffness composite laminates (VSCLs) subjected to a low supersonic airflow. The VSCLs are formed by different individual laminae where polymeric matrix is reinforced curvilinear carbon fibres. plate’s displacement field follows Third-order Shear Deformation Theory (TSDT); p-version finite element employed discretize the components. A full linearized (inviscid, potential flow) aerodynamic theory used approximate pressure. self-exciting vibrational model using principle virtual work. equations motion representing solved Newmark method. Limit cycle oscillations (LCOs) these plates studied time histories, phase-plane plots and FFT spectra. damage onset criterion utilized control structural health during flutter. Effects fibre path angles on linear behaviour, as well in investigated.