Multi-Field Coupled Fluid-Thermal-Structural Analysis Of Hypersonic Wing

Aerothermoelasticity analysis is one of the key technologies of hypersonic vehicle research. Aerothermoelasticity is a typical CFD/CSD/CTD multi-field coupling problem, mainly involving computational fluid dynamics, computational structural dynamics and computational thermal dynamics. Based on a comprehensive review of the aerothermoelasticity analysis method, a multi-field coupling method is used in the paper to actualize the full-coupling analysis by coupling CFD with ANSYS, The main works involving:Model a typical hypersonic wing, and solve the flow field and structure parameters of it respectively by using CFD program and ANSYS software, and complete the data exchange between CFD and ANSYS by the coupling platform. Study on the aerothermoelasticity of the model based on static aerothermoelastic trim and the impact of material properties change and thermal stress on the trim structure. The results show that for this model, the aerodynamic heating makes the structure stiffness, modal frequency decrease and the bending-torsional mode gradually close; the reduction of stiffness is mainly caused by the change of material properties, the influence of thermal stress is small, and the deformation of model is mainly caused by the thermal expansion of materials.Study on the aerothermoelastic response of the model by using the trim results as the initial conditions and appling the perturbation, the results show that the aeroelastic characteristics are changed by aerodynamic heating, and the flutter speed drop significantly, which main caused by the change of material properties.Study on the transient heating problem of the model by using multi-field coupling method and subsection solution, and also investigate the change of structure and aeroelastic characteristics with time along the heating process. The results show that after a period of time, the model reach the state of trim. Along the process, the temperature change rapidly in the initial stage, then gently. The modal frequency decrease gradually with time, rapidly in the initial stage, then tend to the frequency of trim state, and the flutter speed also show the same change trend.