New insights into the nonlinear stability of nanocomposite cylindrical panels under aero-thermal loads

Abstract

In the present study, thermal-aerodynamic postbuckling and thermal flutter behaviors of functionally graded (FG) graphene nanoplatelets (GPLs) reinforced composite (GPLRC) cylindrical panels are theoretically investigated. Homogenization techniques such as the modified Halpin-Tsai model and Voigt’s rule are applied to calculate resultant material properties. The derived model of the cylindrical panel is based on assumptions of the first-order shear deformation theory (FSDT) and von Kármán geometrical nonlinearity. The aerodynamic load induced by the supersonic airflow is determined by the first-order piston theory, whilst the thermal load is based on the quasi-steady thermal stress theory. The element-free improved moving least-square Ritz (IMLS-Ritz) method is applied to develop the nonlinear equations solved with the aid of the Newton-Raphson method. The accuracy and effectiveness of the established numerical model are verified by comparisons with the results from the literature. Effects of key parameters such as aerodynamic pressure, temperature rise, GPL distributions and weight fraction, and geometric properties of cylindrical panels are carried out to comprehensively examine their aerothermoelastic responses. Finally, new insights into the stability of graphene platelet reinforced panels under aerodynamic and thermal loadings are presented and deeply discussed.