| The fluid-thermal-structure coupling problem is an important research content in the hypersonic field.This problem involves the aerodynamic heating of the external flow field of the hypersonic vehicle and the heat transfer of the aircraft structure.The research results have an important impact on the thermal protection performance analysis and structural design of the aircraft,and determine the flight performance and flight safety of the hypersonic vehicle.In this paper,by establishing the wing structure of a hypersonic aircraft,and using the Mp CCI interface software combined with Fluent and Abaqus to form a coupled computing platform,the fluid-thermal-structure coupling problem of the key structure of the hypersonic aircraft was studied.In this paper,by establishing a stainless steel circular tube model,a classic NASA wind tunnel flow experiment was simulated.The shape and position distribution of the shock wave were in good agreement with the experimental results,and the temperature before and after the shock wave is basically consistent with the test results.The accuracy and reliability of the simulation method adopted in this paper were verified by comparing the temperature field distribution of the circular tube structure with the experimental report.Taking the complex structure of hypersonic aircraft wing as the research object,the external flow field distribution of the wing structure at 0° angle of attack and different Mach numbers,as well as the temperature distribution and deformation of the wing structure wall were calculated.The results showed that the total deformation of the wing structure is small when flying at a 0° angle of attack.Relatively speaking,the fatigue damage and ablation effects of temperature and stress on the wing structure should be considered.On the basis of the above research,the effects of different angles of attack on the temperature and deformation of the wing structure under different Mach numbers were studied.The results showed that the angle of attack is the key factor affecting the deformation of the aircraft wing.Especially in the flight conditions of high Mach number and large angle of attack,the heat transfer of the wing structure and the influence of its strain were more prominent.In this paper,MpCCI interface software was used to build a coupled simulation platform to solve the flow-thermal-structure coupling problem of the hypersonic aircraft wing structure.It provides a certain research technique for the research and structural design of the thermal protection system of the hypersonic aircraft wing structure. |
