Method of gas flows calculation in solid propellant rocket engines taking into account the combustion of solid fuel charge

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Method of gas flows calculation in solid propellant rocket engines taking into account the combustion of solid fuel charge	1 MB	Adobe Acrobat PDF	Read	Download
DOI Доступ к ресурсу на сайте издателя			10.1088/1757-899X/597/1/012077

Title: Method of gas flows calculation in solid propellant rocket engines taking into account the combustion of solid fuel charge
Creator: Eremin, Ivan V.
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Kagenov, Anuar M.
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Zhiltsov, Konstantin N.
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Tyryshkin, Ilya M.
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Sereda, M. S.
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Chervakova, A. V.
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Kostyushin, Kirill V.
Date: 2019
DOI: 10.1088/1757-899X/597/1/012077
Description: The paper presents a method for calculating the local and integral characteristics of the flow in the axisymmetric gas-dynamic paths of solid propellant rocket motors, taking into account the combustion of a charge of solid fuel. The numerical method of calculation is based on the use of the Godunov scheme, formulated for moving computational grids. The speed of movement of the combustion surface is defined locally on the edge of each calculation boundary cell. This approach allows us to take into account the uneven distribution of the pressure of the combustion products in the free volume of the combustion chamber. In test calculations, the power law of burning rate is used. Calculations of the gas flow in the solid propellant combustion chamber with cylindrical charge of solid fuel are carried out. Unsteady pressure curve in the combustion chamber is obtained. The method allows to determine all integral characteristics of the developed solid propellant rocket motors as a function of the engine running time

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collection(s): Физико-технический факультет | НИИ прикладной математики и механики
Identifier: смотреть в электронном каталоге НБ ТГУ
Type: статьи в журналах
Source: IOP Conference Series: Materials Science and Engineering. 2019. Vol. 597. P. 012077 (1-6)
Language: eng

Created: 21-01-2020

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Физико-технический факультет Method of gas flows calculation in solid propellant rocket engines taking into account the combustion of solid fuel charge