Research On Aerodynamic Reduced Order Model In Hypersonic

Aerothermoelasticity analysis of hypersonic vehicle is one of the most important direction in aeroelasticity research. It involves subjects like computational fluid dynamics, computational structure dynamics and computational thermodynamics, etc. Usually, CFD/CSD/CTD method is used to solve this typical multi-field coupling issue. In the basis of a comprehensive review in the development of aerothermoelasticity analysis, an efficient reduced order method for aerodynamic and heat flux is introduced. The main work is divided into three parts.Firstly, the fluid and structure models for typical hypersonic wing are built up. Based on this wing, the reduced order model is created. In this thesis, the whole process for the building ARMA/ROM, CFD training, parameters identification and its application in aeroelastic analysis are very well described. With the comparison of CFD result, it shows the correctness and reasonability of this method. Secondly, using reference enthalpy as the reduced order model for the calculation of thermodynamics. It shows, both ARMA/ROM and reference enthalpy can replace CFD method as the reduced model to analysis aeroelasticity.Last but not least, to establish a coupled method with ARMA/ROM and reference enthalpy for aerothermoelasticity analysis. When performing tiny disturbance at any time during the aerodynamic heating process, to solve the transient response by this coupled method. By introducing the concept of temperature modal, to form the new ARMA/ROM on the basis of it. The result shows its advantages in the efficiency of transient response research.