Thermal protection technologies for solid propellant rocket engines
- Authors: Mironov V.V.1, Tolkach M.A.1, Timarov A.G.1,2
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Affiliations:
- State Scientific Center of the Russian Federation “Keldysh Research Center”
- Moscow Aviation Institute (Scientific Research University)
- Issue: Vol 94, No 7 (2024)
- Pages: 677-687
- Section: Review
- URL: https://journals.rcsi.science/0869-5873/article/view/265039
- DOI: https://doi.org/10.31857/S0869587324070083
- EDN: https://elibrary.ru/FLZLEU
- ID: 265039
Cite item
Abstract
The article examines the thermal insulation characteristics of materials used in solid-fuel rocket engines manufactured in the United States, France, Italy, Japan, and other developed nations. The internal surfaces of combustion chambers in these rocket engines are subject to significant stress under thermo-mechanical loading conditions, necessitating specialized protection. The authors identify four categories of reinforced elastomeric materials that most effectively meet stringent requirements. Due to their adaptability, these materials may serve as versatile heat insulators and may be employed in a variety of high-temperature and corrosive surroundings.
Keywords
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About the authors
V. V. Mironov
State Scientific Center of the Russian Federation “Keldysh Research Center”
Author for correspondence.
Email: kerc@elnet.msk.ru
доктор технических наук, заместитель генерального директора по средствам выведения, начальник отделения
Russian Federation, MoscowM. A. Tolkach
State Scientific Center of the Russian Federation “Keldysh Research Center”
Email: tolkach@kerc.msk.ru
кандидат технических наук, ведущий научный сотрудник
Russian Federation, MoscowA. G. Timarov
State Scientific Center of the Russian Federation “Keldysh Research Center”; Moscow Aviation Institute (Scientific Research University)
Email: Timarov@kerc.msk.ru
кандидат технических наук, ведущий научный сотрудник, доцент
Russian Federation, Moscow; MoscowReferences
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