Abstract
The analysis of thermo-structural behaviour is crucial to the nose cap of a hypersonic vehicle under aerothermodynamic loads. Considering chemical nonequilibrium of the flow field, heat transfer, and deformation of the structure, a fluid-thermal-structural coupling model of the typical nose cap was established. The coupling relation between the flow field and nose cap was analyzed. The results show that the fluid-thermal-structural model can effectively predict the response of the nose cap under a hypersonic environment. The highest temperature and the peak of maximum principal stress appear at the front of the nose cap at an initial stage. As time goes on, the highest temperature increases gradually and the peak of maximum principal stress decreases after reaching a certain value. The position of the peak of maximum principal stress gradually moves to the inside of the nose cap and eventually stabilizes. With the increase in the Mach number, the highest temperature and the peak of maximum principal stress of the nose cap increase. The fluid-thermal-structural coupling model can provide guidance for the optimal design of the nose cap of a hypersonic vehicle.
Highlights
The hypersonic flight within the atmosphere can result in severe aerodynamic heating phenomena, which poses a major challenge for the thermal protection design of hypersonic vehicles [1]
When the nose cap is subjected to the aerothermodynamic loads, high temperature of the structure will cause the change of material physical parameters and large temperature gradient will result in thermal stress and deformation
A fluid-thermal-structural model was established to study the response of the nose cap in a hypersonic environment
Summary
The hypersonic flight within the atmosphere can result in severe aerodynamic heating phenomena, which poses a major challenge for the thermal protection design of hypersonic vehicles [1]. It is necessary to establish a fluid-thermal-structural coupling model to predict the hypersonic flow field, transient temperature, and deformation of the nose cap. In. References [7, 8], the coupling model of the nose cap and hypersonic flow was established, and the effect of an attack angle on the nose cap response was analyzed. Took the spine blunt body of aircraft as the research object, established the fluid-thermal-structural coupling model, analyzed the thermal response of the model, and obtained that the blunt body with longer spike had better thermal protection performance [15]. In most of the previous researches on the response of the nose cap, a one-way coupling method was adopted, ignoring the influence of structural response on aerothermodynamic loads, which will affect the accuracy of prediction results. The numerical results are expected to provide technical support to the nose cap design of a hypersonic vehicle
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