Analysis Of Aeothermoelastic Behavior Of Hypersonic Wing Based On Multi-field Coupled Method

Aerothermoelastic behavior in hypersonic flow is receiving more and more attention with thedevelopment of hypersonic vehicles. The problem involving nonlinear aerodynamic, aerodynamicheating, structure thermal conduction and radiation, which is in excess of traditional aeroelasticity,should be solved with a multidisciplinary method including CFD, CSD and CTD. In this dissertation,a research is carried out on aerothermoelasticity problem based on multi-field coupled method.ANSYS CFX is chosen as the solver of the non-equilibrium chemical reaction Navier-Stokesequation to get precise aerodynamic force of hypersonic flow. Also its discretization and solutiontheory is introduced. Some examples are given to verify the capability of solving pressure, heat fluxand non-equilibrium chemical reaction in hypersonic flow.The concept and method of multi-field coupled analysis and some key technologies such asdynamic mesh, interpolation method are introduced. The solving method is achieved by secondarydevelopment of software after an analysis model being presented. Some examples are used to verifyits reliability.At last, a complete analysis process is presented to study the aerothermoelasticity of a typicalhypersonic wing. The deformation and temperature distribution of the wing are obtained after thestatic aerothermoelastic trim. The prestressed modal analysis shows that the natural frequencies arechanged with a combined action of aerodynamic force and heating, which influence the dynamicstability of structure. After analyzing the vibration response of disturbed structure, the critical velocityof flutter is given. The results show that the method can deal with the aerothermoelastic problem ofhypersonic vehicle quite well; the calculation provides reference for research and engineering.