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1 840 812

(13)

(51)

IPC

F02K9/26(2006-01-01)

(21) (22)

Application

3107178/06, 1985-02-01

(22)

Actual filing date

1985-02-01

(45)

Published

2010-12-27

(72)

Inventor

Gerasimov V.A.Strukov S.I.Pozdnjakov V.V.Klimov V.B.Kruglov S.V.Ehrmant A.S.Timoshkin G.M.Trapeznikov N.I.

SOLID PROPELLANT ROCKET ENGINE Russian patent published in 2010 - IPC F02K9/26

Abstract SU 1840812 A1

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to the field of rocket engines operating on low-smoke solid propellant and intended for small-scale missiles controlled under conditions of direct optical visibility. Solid propellant rocket engine comprises casing that includes channel charge, additional bomb of high-energy fuel, gas dynamic stabiliser and igniter. Channel charge is arranged with a cylindrical bore at the side opposite to the nozzle unit and includes radial slots. Gas dynamic stabiliser is arranged in the form of a cylindrical chamber with radial calibrated holes and is installed at the back bottom in cylindrical bore of charge with a circular gap. Additional bomb is arranged in gas dynamic stabiliser, and igniter is fixed coaxially to channel of charge at its end. Total area of calibrated holes of gas dynamic stabiliser equals 0.0014-0.002 of initial surface of charge burning, area of circular gap equals 0.95-1.05 of total area of entry to radial slots, and ratio of bore diameter to charge channel diameter equals to 1.6 - 2.

EFFECT: invention makes it possible to improve reliability of solid propellant rocket engine operation.

2 cl, 4 dwg

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SU 1 840 812 A1

Authors

Gerasimov V.A.

Strukov S.I.

Pozdnjakov V.V.

Klimov V.B.

Kruglov S.V.

Ehrmant A.S.

Timoshkin G.M.

Trapeznikov N.I.

Dates

2010-12-27—Published

1985-02-01—Filed