SOLID PROPELLANT ROCKET ENGINE NOZZLE BLOCK INSERT MADE OF CARBON-SILICA COMPOSITE MATERIAL Russian patent published in 2021 - IPC F02K9/97 F02K9/32 

Abstract RU 2746081 C1

FIELD: rocketry.

SUBSTANCE: invention relates to solid propellant rocket engines (SPREs) and namely to rocket nozzles and can be used in the SPRE nozzle unit for passive thrust control. The liner of the nozzle unit of a solid propellant rocket engine has a three-dimensional volumetric frame which is woven from a composite thread consisting of carbon and silica filaments and filled with pyrocarbon. Changing the ratio of the proportions of carbon and silica filaments in the volumetric frame contributes to an increase in the critical section area of the liner from 50 to 100% of the initial value.

EFFECT: invention maintains a constant pressure level of combustion products and helps to obtain intraballistic characteristics. The invention also enables use of rocket fuels with a combustion temperature of more than 4000 K due to the fact that the liner of the nozzle unit is made of material with controlled and planned erosion resistance.

1 cl, 1 tbl, 1 dwg

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RU 2 746 081 C1

Authors

Ershov Anatolij Mikhajlovich

Karsakov Aleksandr Sergeevich

Myshkin Sergej Nikolaevich

Podkopaev Aleksandr Sergeevich

Balakhonov Yurij Andreevich

Dates

2021-04-06Published

2020-02-11Filed