On the efficiency of using the Navier-Stokes approximation in thermogasdynamic calculation of low-thrust liquid-propellant rocket engines at low Reynolds numbers

A numerical method for thermogasdynamic calculation of low-thrust liquid rocket engines is presented. These engines are used as end organs of the system of space attitude control for nanosatellites and small spacecraft. The method is based on the use of the TERRA software package for thermodynamic c...

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Published inVestnik Samarskogo universiteta. Aèrokosmičeskaâ tehnika, tehnologii i mašinostroenie (Online) Vol. 21; no. 1; pp. 67 - 80
Main Authors Maksimov, A. D., Shustov, S. A.
Format Journal Article
LanguageEnglish
Published Samara National Research University 27.04.2022
Subjects
low-thrust liquid-propellant rocket engines
mach number
navier-stokes equations
propulsion unit
reynolds number
specific impulse
specific impulse loss
thermogasdynamic calculation
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Summary:A numerical method for thermogasdynamic calculation of low-thrust liquid rocket engines is presented. These engines are used as end organs of the system of space attitude control for nanosatellites and small spacecraft. The method is based on the use of the TERRA software package for thermodynamic calculation and the Ansys CFX software package for gas-dynamic calculation using the Navier-Stokes equations. The results of the thermogasdynamic calculation, as well as the flow pattern of the working fluid in the chamber, are presented. The results of validating the described method are also presented. Its capabilities and limitations are analyzed. The validation procedure is based on the comparison with the results of experimental data on the Reynolds number and the momentum thickness.
ISSN:2542-0453
2541-7533
DOI:10.18287/2541-7533-2022-21-1-67-80