Numerical method for hypersonic aerothermoelasticity

Based on the characteristics of aerothermoelasticity, the loose coupling method is used to establish the aeroelastic model. The analysis consists of the following four steps: aerodynamic heating computation, structure's temperature distribution computation, thermal-vibration analysis and aeroelasticity analysis. The aeroelasticity involving thermal effect of the given temperature distribution is analyzed. With the uncoupled thermal-structure analysis method and the consideration of the additional stiffness caused by thermal stress, a finite element model for thermal-vibration analysis is obtained and two typical hypersonic wing structures are studied. Using local piston theory based on CFD to solve hypersonic unsteady aerodynamic loads, the hypersonic aerothermoelasticity is simulated in time domain. The influences of temperature and the structure's supporting conditions on aerothermoelastic systems are analyzed.