Nonlinear flutter of orthotropic composite panel under aerodynamic heating

Abstract

The problem of nonlinear aerothermoelasticity of isotropic and specially orthotropic panels in supersonic airflow is examined. The Reissner functional is used with Hamilton's principle to derive the governing equations of motion, the constitutive relations, and the natural boundary conditions. The work done by aerodynamic forces is represented by using the «piston» theory for two-dimensional lifting surfaces. The aerodynamic heating effect is estimated on the basis of the adiabatic wall temperature due to the high-speed airstream. Galerkin's method is then applied