Flutter reliability analysis of laminated composite plates

Composite materials are widely used in modern aerospace flight vehicles, especially because of their high specific strength and lightweight than other materials. Since the study of reliability and uncertainty of composite material design variables in aeroelasticity has received less attention, in the present work the reliability of the laminated composite plate due to uncertainty in variables including elastic model, Poisson coefficient, density, thickness, and length is examined. The composite laminated plate is symmetric with different boundary conditions subjected to supersonic airflow. The classical plate theory and the first-order piston theory are utilized to derive the equation of motion. The differential quadrature method has been used to discretize and analyze the aeroelastic equations. The governing equations after discretization are solved by calculating and analyzing eigenvalues and the occurrence of the flutter phenomenon for the laminated composite plate is obtained. To examine the reliability, the distribution of random variables as a normal distribution has been used. Finally, the Monte Carlo simulation method was used for five different boundary conditions to obtain the reliability of the plate flat threshold. According to the presented results, the reliability value of the composite plate flutter threshold for the full hinge boundary condition (SSSS) will be higher than other boundary conditions and the all-bound boundary condition (CCCC) will be lower than other boundary conditions. Also, according to the studies on the condition of the fiber angle of the composite plate, it can be concluded that increasing the angle of the fiber of the composite plate increases the reliability of the occurrence of the filter threshold.