Satellite electric propulsion system xenon filling thermodynamic characteristic numerical simulation method

Abstract

The invention relates to a satellite electric propulsion system xenon filling thermodynamic characteristic numerical simulation method which includes the following steps: step S101, xenon fluid state equations are established, the xenon fluid state equations include Redlich-Kwong equation, BWR equation and Helmholtz equation for using least square method numerical interpolation fitting to establish thermodynamic properties, the three different types of empirical parameter equations are compared and analyzed; step S102, according to thermodynamic parameters of xenon in a particular state or region range, one or more of the three different types of empirical parameter equations of the RK equation, the BWR equation and the Helmholtz equation is/ are selected; and step S103, xenon filling thermodynamic characteristic numerical simulation can be performed by setting of the simulation parameters. The satellite electric propulsion system xenon filling characteristic numerical simulation method can simulate satellite electric propulsion system xenon filling characteristics, test and estimate xenon filling total temperature and total pressure range numerical simulation, and has the advantages of strong adaptability, high precision and easiness in use.

Description

technical field [0001] The invention relates to a numerical simulation test method, in particular to a numerical simulation method for thermodynamic characteristics in the xenon filling and filling process of a satellite electric propulsion system. Background technique [0002] The working medium of the satellite electric propulsion system is xenon gas. Due to the special physical properties of xenon gas such as large molecular weight, high melting point, high boiling point and high critical point, there are many unknowns in the charging of the working medium xenon gas in the electric propulsion system, filling at the launch site, and on-orbit storage and use. Factors, high safety risks, technical difficulties in ground storage, testing, filling and on-orbit storage of xenon gas, and no corresponding basic test data, while satellite electric propulsion system xenon has a wide range of ground test and filling process parameters, At present, it is impossible to conduct physica...

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Problems solved by technology

[0002] The working medium of the satellite electric propulsion system is xenon gas. Due to the special physical properties of xenon gas such as large molecular weight, high melting point, high boiling point and high critical point, there are many unknowns in the charging of the working medium xenon gas in the electric propulsion system, filling at the launch site, and on-orbit storage and use. Factors, high safety risks, technical difficulties in ground storage, testing, filling and on-orbit storage of xenon gas, and no corresponding basic test data, while satellite electric propulsion system xenon has a wide range of ground test and filling process parameters, At present, it is impossible to conduct physical tests on the thermodynamic properties of xenon gas in the whole process range at home and abroad, and it is also impossible to obtain the test data on the thermodynamic properties of xenon gas in the whole process range. However, satellite filling and launch site filling have a great impact on the internal t

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