A Method for Discriminating the Occurrence Conditions and Types of Spacecraft Body Shock/Front Shock-like Interference

Abstract

The invention relates to a method for determining interference-producing conditions and types of shock waves / leading-edge type shock waves of a spacecraft body, pertaining to the field of spacecraft aerodynamic heat environment analyses. The method comprises following steps: establishing quantitative relations between interference-producing conditions for body shock waves / leading-edge type shock waves and flying states and aerodynamic configuration according to shock relations and rapidly determining interference-producing conditions for body shock waves / leading-edge type shock waves and giving interference-producing positions; establishing associated relations between interference type determination parameters for body shock waves / leading-edge type shock waves, and flying states and aerodynamic configuration parameters and rapidly determining according to different types of interference flow structure features of body shock waves / leading-edge type shock waves and rapidly determining types of interference. The method is capable of shortening determination cycles of interference-producing conditions for body shock waves / leading-edge type shock waves so that determination difficulty is reduced and design efficiency is increased.

Description

Technical field: [0001] The invention relates to a method for judging the occurrence conditions and types of spacecraft shock wave / shock wave interference, in particular to a method for generating interference occurrence conditions and methods for body shock waves and front-edge shock waves through the flight state and aerodynamic shape of high-speed spacecraft. The method for quickly distinguishing the type belongs to the field of spacecraft aerodynamic thermal environment analysis. Background technique: [0002] High-speed spacecraft usually have components such as horizontal wings, vertical stabilizers, and control rudders. The head shock wave extends toward the body, and may intersect with the leading edge detachment shock wave of the above-mentioned components, resulting in body shock / leading edge-like shock waves. wave interference. The body shock wave / leading edge shock wave interference will affect the local heat flow, and may pose a threat to flight safety in sever...

AI Technical Summary

Problems solved by technology

However, body shock / front-edge shock-like interference produces a complex wave system structure including shock waves and shear layers in the flow field, which manifests in many different forms. The traditional type definition is for complex body Shock wave / front-edge shock wave interference is difficult to apply

[0003] In addition, the existing shock wave / shock wave interference type discrimination method needs to obtain detailed information of the shock wave interference structure through numerical simulation or ground test in order to discriminate the shock wave / shock wave interference type and action location, and accurately obtain the shock wave The detailed information of the interference structure puts forward very high requirements on the number, quality, simulation accuracy of the numerical simulation grid and the ability to capture the flow field structure of the test; while the identification of the conditions for the shock wave interference requires a large number of numerical simulations in different states or ground test to obtain

The above method leads to a long and difficult period of identifying the occurrence conditions and types of body shock wave / leading edge shock wave interference, and it is difficult to provide thermal constraints for the overall and aerodynamic shape design in the scheme design stage

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