Integrated analysis of aerothermal-aeroelastic wings in hypersonic flow

To research the static aeroelastic problems of the hypersonic vehicles in which the thermal effects must be considered, the rapid analysis of the hypersonic vehicles from aerodynamic heating to static aeroelasticity was developed. A hierarchical solution process was used to dealing with the aerothermal-aeroelastic coupling problems. The whole flow field was divided into inviscid flow field out of the boundary layer and viscous field inside the boundary layer, and the method simulating the inviscid flow field numerically and predicting the viscous field experientially was used to compute the hypersonic aerodynamic heating and the temperature field. The stress stiffness matrix under this temperature field was developed. A hypersonic low aspect-ratio wing was researched, and the temperature field, thermal stress, thermal stiffness and static aeroelastic characteristic of the wing was computed. Therefore, the feasibility and applicability of this aerothermoelastic rapid analysis is demonstrated.