Multi-field coupling transient numerical method for hypersonic flow-heat transfer and structural response

Abstract

The invention discloses a multi-field coupling transient numerical method for hypersonic flow-heat transfer and structural response. The method comprises the following steps of: determining wall temperature and displacement boundary condition according to structure, performing data exchange at a fluid-solid coupling interface, and obtaining the current temperature and displacement boundary condition; simultaneously solving coupled solution format of each preset conservation equation to obtain the current heat flux and pressure; performing data exchange at the fluid-solid coupling interface to obtain the boundary condition of a solid region; according to the boundary condition of the solid region, solving out the wall temperature and structure displacement through a thermal mechanical unity coupling method; and executing the steps above repeatedly until meeting a preset stop condition. Using the method provided by the invention, multi-field coupling calculation where a hypersonic non-equilibrium flow solver and a structural thermal/mechanical unity coupling solver are coupled is realized, prediction on pneumatic thermodynamic environment and structural thermodynamic response of a hypersonic aircraft meets physical reality better, and calculation precision can be guaranteed.

Description

technical field [0001] The invention relates to the technical field of modern high-speed aircraft design, in particular to a multi-field coupling transient numerical method of hypersonic flow-heat transfer and structural response. Background technique [0002] The rapid development of hypersonic vehicles has brought more severe challenges to thermal protection design. Accurately predicting the aerodynamic thermal / mechanical environment, structural temperature and stress state can improve the safety performance of the aircraft while reducing the design redundancy of the thermal protection system, which is of great significance to improving the performance of the aircraft. [0003] In the prior art, the prediction of the thermal / mechanical load environment of traditional hypersonic vehicles and the analysis of the thermal protection structure performance are basically still in a state of separation. The methods in the prior art generally perform fluid calculations under given...

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Problems solved by technology

However, due to the complexity of multi-physics coupling problems, further research on analytical methods is

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