Design Oriented Aeroelastic Analysis of Hypersonic Vehicles Including Internal and External Radiation Effects

A methodology for obtaining shape sensitivities of flutter eigenvalues of aerothermoe-lastic structures is presented. The response is based on a coupled aero-thermal-structural multidisciplinary analysis. Thermal analysis includes nonlinear transient heat conduction with radiation on the external wing surface and inside the internal cavities of the structure. Thermal effects are included in structural analysis through dependence of material prop-erties on temperature and through geometric effects due to thermal stresses. Numerical test cases include panel flutter and a low aspect ratio wing box. Parametric flutter studies are performed for the wing box with respect to a design variable and the sensitivity results are shown for the multidisciplinary problem. I