Effect of structural thermal boundary on areothermoelasticity for hypersonic vehicles

The effect of structural thermal boundary on aerothermoelasticity of hypersonic all-movable control surface/wing is studied on the basis of hierarchical solution process. On the basis of CFD technology, Navier-Stokes equation is solved to get the thermal environment. And then transient thermal conduction of structure is analyzed. Then structural modal is analyzed under the effect of structure's thermal stress caused by temperature gradient and material property decrease caused by high temperature, then structural mode is interpolated to the aerodynamic grid; Finally, Euler equation is solved to get flow parameter, and based on CFD local piston theory, aerothermoelasticity is analyzed in state space. Through analyzing aerothermoelasticity of four different structural models, the effect of the structural thermal boundary on aerothermoelasticity of all-movable control surface/wing is analyzed. The results show that: for the control surface in this paper, the structural thermal boundary would firstly affect the heat transfer process and temperature distribution of shaft structure. The effect on the variation of the natural frequency, frequency spacing, flutter velocity and flutter frequency is about 16%. For the wing in this paper, The effect on the variation of the natural frequency, frequency spacing, flutter velocity and flutter frequency is about 1%. Therefore, in practical engineering, reasonable thermal boundary should be used while analyzing aerothermoelasticity.