Samara University Repository
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This is an open electronic archive created to preserve and disseminate the scientific results of our university. The works of researchers, faculty members, and students are available to everyone for academic and research purposes.
The repository contains dissertations, research articles, educational and methodological materials, monographs, and regulatory documents. The collections cover a wide range of fields: from aerospace technologies, engine engineering, and computer science to history, linguistics, mathematics, and ecology. The archive brings together the scientific heritage of the university, including materials prepared during the period of Samara State Aerospace University and Samara State University.
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| Title: | Анализ особенностей расчета теплового состояния маршевого ЖРД разгонного блока тягой 6 кН на жидких компонентах топлива: высококонцентрированная перекись водоро |
| Authors: | Гильманова А. Н. |
| Keywords: | calculation methods CFD models CFD-модели liquid rocket engines specific impulse value thermal state calculation thermodynamic design thermogasdynamic calculation величина удельного импульса жидкостные ракетные двигатели методики расчета расчет теплового состояния термогазодинамический расчет термодинамическое проектирование |
| Issue Date: | 2025 |
| Citation: | Гильманова, А. Н. Анализ особенностей расчета теплового состояния маршевого ЖРД разгонного блока тягой 6 кН на жидких компонентах топлива: высококонцентрированная перекись водорода и керосин = Analysis of the features of calculating the thermalstate of the rocket engine of the upper stage with a thrust of 6 kN on liquid fuel components: highly concentrated hydrogen peroxide and kerosene / А. Н. Гильманова // Перспективы развития двигателестроения : материалы междунар. науч.-техн. конф. им. Н. Д. Кузнецова (18–20 июня 2025 г.) / Самар. нац. исслед. ун-т им. С. П. Королева (Самар. ун-т) ; редкол.: Е. В. Шахматов, А. И. Ермаков. - Самара : Изд-во Самар. ун-та, 2025. - С. 1036-1038. |
| Abstract: | The study presents the results of analyzing thermal state calculation methods for a 6 kN thrust upper-stage liquid rocket engine using highly concentrated hydrogen peroxide and kerosene as propellants. |
| URI: | http://repo.ssau.ru/jspui/handle/123456789/43187 |
| Appears in Collections: | Перспективы развития двигателестроения |
| File | Size | Format | |
|---|---|---|---|
| 978-5-7883-2191-2_2025-1036-1038.pdf | 381.99 kB | Adobe PDF | View/Open |
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