Thermal protection systems for combined rocket-ramjet solid fuel engine

Thermal engines, electric propulsion and power plants for flying vehicles


Аuthors

Kopylov A. V.1*, Tikhomirov М. A.1**, Mokretsova O. V.2***

1. Engineering Design Bureau”Iskra” named after Ivan Kartukov, 35, Leningradskoe shosse, Moscow, 125284, Russia
2. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: alexcopylov@mail.ru
**e-mail: mishata84@mail.ru
***e-mail: moolia87@mail.ru

Abstract

On the basis of multifactorial analysis, computational research and tests carried out constructively-similar samples developed the following thermal protection system structures of a combined rocket-ramjet engine solid fuel (KRPD-T):

  • thermal protection system with increased thermo-erosive strength for gas generator and combustion chamber KRPD-T under conditions of exposure of high-speed (up to 400 m/s) and high-temperature flow of combustion products, made in the form of an elastic inner ablative thermal barrier coatings consisting of a reinforcing filler (tissue, fibers) and polymer binder. The effect of heat protection is that under the influence of high temperatures, the polymeric phenol-formaldehyde binder begins to break down. This process is accompanied by absorption of heat due to the endothermic effect of the decomposition reaction components inner ablative thermal barrier coatings with subsequent removal of the product stream of the gas generation, which makes inner ablative thermal barrier coatings heat resistant, and its ablation managed;

  • thermal protection system details of fuel consumption regulator, in the form of carbon-carbon composite materials (CCCM) with a protective ceramic coatings, applied surface silicononane; CCCM partial introduction of silicon carbide in the volume or CCCM surround silicononane that allows you to get the item from carbon-ceramic composite material;

  • thermal protection system details of the flowing part KRPD-T in the form of hard thermal barrier coating composite fiber of press materials (fiberglass plastics, hybrid carbon and glass fiber textolites).

Also in work the analysis of use on the outer surface of the housing KRPD-T outer thermal barrier coatings — based low molecular weight silicone rubber to protect against aerodynamic heating. Study outer thermal barrier coatings outdoor temperature is confirmed by testing structurally similar samples.

The system of thermal protection allow you to:

  • to increase the working time of parts and housings KRPD-T;

  • enhance the tactical and technical characteristics of missiles with KRPD-T.

Keywords:

thermal protection system, rocket ram-jet engine of solid fuel, external and internal elastic thermal protective coatings, carbon-carbon composite materials with surface and volume silicization, carbon-ceramic composite materials

References

  1. Sorokin V.A., Kopylov A.V., Tikhomirov M.A., Stirin E.A., Loginov A.N., Fedorov D.Yu., Valui P.V. Trudy MAI, 2015, no. 84, available at: http://trudymai.ru/eng/published.php?ID=63029

  2. Stirin E.A., Loginov A.N., Tikhomirov M.A. Trudy MAI. 2014. № 74. URL: http://trudymai.ru/eng/published.php?ID=49307

  3. Mikhatulin D.S., Polezhaev Yu.V. Materialy V Minskogo mezhdunarodnogo foruma po teplo — i massoobmenu, Minsk, 2004, vol. 1, pp. 318-319.

  4. Mikhailovskii K.V., Timofeev I.A., Reznik S.V. Konstruktsii iz kompozitsionnykh materialov, 2011, no. 1, pp. 18-30.

  5. Vasil’ev V.V., Tarnopol’skii Yu.M. Kompozitsionnye materialy (Composite materials), Moscow, Mashinostroenie, 1990, 512 p.

  6. Baskakov V.N., Kopylov A.V., Semenova A.N. Patent SU 94102, 10.05.2010.

  7. Polezhaev Yu.V., Yurevich F.B. Teplovaya zashita (Thermal protection), Moscow, Energiya, 1976, 392 p.


Download

mai.ru — informational site MAI

Copyright © 2000-2019 by MAI

Вход