System of pressurization of the fuel tank of a launch vehicle using the heat of generator gas

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Abstract

Comparative analysis of heat exchangers of various types is carried out: crossflow, shell- and- tube, plate heat exchangers. Mass- power characteristics of the three types of heat exchangers are calculated.

About the authors

V. V. Biryuk

Samara State Aerospace University

Author for correspondence.
Email: teplotex_ssau@bk.ru

Doctor of Engineering Science

Professor of the Heat Engineering Department

Russian Federation

A. V. Smorodin

SPACE ROCKET CENTER «TsSKB-PROGRESS», Samara

Email: lex.samara@rambler.ru

Chief Designer of the Launch Vehicle «Soyuz-2-1v»

Russian Federation

A. I. Shepelev

SPACE ROCKET CENTER «TsSKB-PROGRESS», Samara

Email: uran_74@mail.ru

Deputy Chief Designer

Russian Federation

D. A. Onoprienko

SPACE ROCKET CENTER «TsSKB-PROGRESS», Samara

Email: den_ssau@mail.ru

Design Engineer

Russian Federation

References

  1. Двигательные установки ракет на жидком топливе [Текст]/под ред. О.Н. Прядкина. – М.: Мир, 1966. – 404 с.
  2. Добровольский, М.В. Жидкостные ракетные двигатели [Текст]/М.В. Добровольский – М.: МГТУ им. Н.Э. Баумана, 2005. – 488 с.
  3. Коваленко, Л.М. Теплообменники с интенсификацией теплоотдачи [Текст] /Л.М. Коваленко, А.Ф. Глушков. – М.: Энергоатомиздат, 1986. – 240 с.
  4. Фраас, А. Расчет и конструирование теплообменников [Текст]/А. Фраас, М. Оцисик – М.: Атомиздат, 1971. – 361 с.

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