AEROTHERMOELASTICITY ANALYSIS OF HYPERSONIC VEHICLE BASED ON MESHFREE METHOD

During the flight, hypersonic vehicles are subject to severe aerodynamic heating. It is necessary to consider the close coupling between aerodynamics/structure/heat, which is complicated to a certain extent. The difficulty of introducing thermal effects into pneumatic/structural coupling analysis is that there is a large difference in time scale between thermal conduction analysis and aerodynamic/structural coupling analysis. Based on the finite element method, aero-structure-thermo coupling analysis methods for hypersonic aircraft are quite mature, but certain disadvantages exist in terms of analysis time consumption. The rapid analysis method based on the meshfree method can improve calculation efficiency and ensure the accuracy of analysis results.In this paper, when refer to the rudder surface components, the thermal conduction analysis and structural static analysis methods in the aero-structure-thermo coupling analysis framework are replaced with a meshfree method. By storing the static analysis stiffness matrix and transient thermal conductivity stiffness matrix in advance, a rapid aero-structure-thermo coupling analysis method with the basis of the meshfree method is formed to obtain surface pressure, heat flow, temperature distribution, and aerothermoelasticity elastic response. This paper verifies the effectiveness of the meshfree method under the comparison of the results of the traditional finite element method and the meshfree method. While the meshfree method greatly reduces the time required for analysis, it has a certain degree of accuracy as well. The analysis results show that the thermal environment has a great influence on structural deformation. When the structural rigidity is on the high level, the thermal deformation far exceeds the aerodynamic elastic deformation. In the aero-structure-thermo coupling analysis of hypersonic aircraft, the influence of the thermal environment shall be taken into consideration.