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

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.

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