Method, device, electronic equipment and medium for predicting heat flow at stagnation point of Mars entry vehicle

Abstract

The application discloses a method, device, electronic equipment and medium for predicting stagnation point heat flow of a Mars enterer. The method may include: determining the geometry and flow field characteristic quantities of the enterer, and then determining multiple sets of state combinations; calculating the thermochemical non-equilibrium flow field of the Martian atmosphere for each set of state combinations, calculating the heat flow value at the stagnation point, and obtaining a sample data set ; Build a neural network model, and train the neural network according to the sample data set to obtain the final neural network model; predict the convective heat flow at the stagnation point through the final neural network model. The invention is based on grid debugging and preliminary calculation of the mean molecular free path, and based on key technologies such as neural network training, so as to realize accurate and rapid prediction of heat flow at the stagnation point of the Mars enterer.

Description

technical field [0001] The invention relates to the technical field of aerodynamic thermal environment simulation, and more specifically, to a method, device, electronic equipment and medium for predicting stagnation point heat flow of a Mars enterer. Background technique [0002] Mars is the closest planet to Earth and the most explored planet in the solar system. Humans have explored Mars for nearly 60 years. Only 7 of the previous 15 Mars landing missions were successful. Most of the failed missions occurred in the descent and landing phase of the probe, namely EDL (Entry-Descent-Landing), so this process is the key to the success or failure of the mission. [0003] In the entry phase of the Mars exploration EDL process, the problems faced come from the special atmospheric composition and thin environment of Mars. new requirements. Insufficient understanding of the nature of the Martian atmosphere and insufficient ability to predict the aerodynamic and thermal character...

AI Technical Summary

Problems solved by technology

Insufficient understanding of the nature of the Martian atmosphere and insufficient ability to predict the aerodynamic and thermal characteristics of Mars entry lead to large uncertainties in the orbit design and thermal protection system design of early Mars entry vehicles, resulting in the fact that the aerodynamic parameters in the actual entry process are often very different. Easily exceed design values ​​or encounter poorly understood physical phenomena, which eventually lead to mission failure

In the literature, Wright reviewed the development and application of the aerothermodynamic model. At present, the uncertainty of the prediction of the aerothermal environment of the Mars enterer has been greatly improved. However, in the engineering design, the thermal protection system of the enterer requires a large number of orbit states The thermal environment data corresponding to the point is used for design, and the calculation of the thermochemical non-equilibrium flow in the Martian atmosphere consumes computing resources and takes a long time, which cannot meet the engineering requirements

Therefore, engineering methods are often used to give the stagnation point heat flow value, but the engineering method is generally a simple fitting formula based on the boundary layer theory. reflect the non-equilibrium nature of the flow

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