Aeroelastic flutter of actively controlled nanocomposite beams with an open edge crack

Active control of aeroelastic flutter in composite structures is vital for improving the performance and safety of aerospace systems. Understanding the impact of cracks on flutter behavior of active controlled structures is of importance for early crack detection and accident prevention. The present work investigates the aeroelastic flutter of functionally graded (FG) graphene nanoplatelet (GNP)-reinforced nanocomposite (GNPRC) beams containing an edge crack under active control with an attached piezoelectric patch. The governing differential equations are derived using Hamilton's principle together with the Ritz method, based on the first order shear deformation theory (FSDT) and a rotational spring model. The flutter velocities of the system are determined by numerically solving the eigenvalue problem. Through a comprehensive parametric study, the effects of crack length and location, GNP parameters, and different control actions on the flutter velocities of the FG-GNPRC beams with different end supports are discussed. The results reveal that the presence of a crack reduces the flutter velocities of GNPRC beams, with the extent of reduction depending on the GNP distribution pattern, crack location and support ends. Additionally, the cracked GNPRC beams can be enhanced by attaching piezoelectric actuators with feedback gains at appropriate locations on the beam's surface.