Mathematical model of small-thrust rocket engine with gaseous oxygen and hydrogen in pulse operation

Cover Page

Cite item

Full Text

Abstract

Is indicated that working substance in combustion chamber corresponds a variable-mass and variable-composition body. Its variation is described with calculation equations for variable-mass and variable-composition body thermodynamics. System of equations for calculation combustion products equilibrium composition is composed. Mathematical model of small-thrust rocket engine which allows to determine ideal engines parameters for pulse mode is designed.

About the authors

1 1

Samara State Aerospace University

Author for correspondence.
Email: sadohina@ssau.ru
Russian Federation

References

  1. Егорычев, В.С. Метод расчета процессов в термодинамике тела переменных массы и состава / В.С. Егорычев // Вестник СГАУ: Специальный выпуск. Труды МНТК «Проблемы и перспективы развития двигателестроения».– Самара: СГАУ, 2003.
  2. Термодинамические свойства индивидуальных веществ: Справочник в 4 т./ Под ред. акад. В.П. Глушко.– М.: Наука, 1978–1982.
  3. Термодинамические и теплофизические свойства продуктов сгорания: Справочник в 10 т./ Под ред. акад. В.П. Глушко.– М.: ВИНИТИ АН СССР, 1971–1979.

Supplementary files

Supplementary Files
Action
1. JATS XML

Copyright (c) 2015 VESTNIK of the Samara State Aerospace University

This website uses cookies

You consent to our cookies if you continue to use our website.

About Cookies