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Hypersonic vehicle simulation is complicated due to coupling between aerodynamics, the propulsion system, heat transfer due to aerodynamic heating, and structural deformations. The high speed involved in hypersonic flight results in the existence of a large heat flux at the vehicle surface. Heat transfer through the internal structure leads to temperature gradients that load the structure due to differential thermal expansion. Additionally, the structure is loaded by aerodynamic pressure. Of particular interest in this study is the extent to which structural deformation alters aerodynamic performance as it relates to vehicle control. As the control surfaces are expected to produce a significant portion of the aerodynamic forces and moments on the vehicle, this paper will focus on the integrated aerothermoelastic modeling of such a structure with the goal of evaluating the effect of structural elasticity on flight dynamics and control system performance. The Eckert reference temperature method is used to calculate the aerodynamic heat flux boundary condition at the surface and finite element representations are used to calculate the temperature distribution and structural displacements. The aerodynamic pressures over the deformed configuration are found using the analytical oblique shock/expansion fan relations. The resulting pressures are integrated over the surfaces to calculate the total lift and drag. For the trajectory points considered, the maximum relative change in lift and drag were found to be 2% and 6%, respectively. A lift-based trim routine is outlined for use in assessing the control surface deflections required to account for the change in aerodynamic lift and drag.

Thermoelastic Formulation of a Hypersonic Vehicle Control Surface for Control-Oriented Simulation