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2 125 175

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C1

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IPC

(21) (22)

Application

98103167/06, 1998-02-20

(22)

Actual filing date

1998-02-20

(45)

Published

1999-01-20

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Inventor

Obozov L.I.Kashirkin A.A.Peturkin D.M.Semilet V.V.Makarovets N.A.Kutsenko G.V.Nekrasov V.I.Shevrikuko I.D.Amarantov G.N.Smirnov V.D.Kuz'Mitskij G.Eh.Vronskij N.M.Lisovskij V.M.Grinberg S.I.Makarov L.B.Filatov V.G.

(73)

Holder

Permskij Zavod Im.S.M.KirovaNauchno-Proizvodstvennoe Ob"Edinenie Im.S.M.Kirova

SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 1999 - IPC

Abstract RU 2125175 C1

FIELD: rocket engines. SUBSTANCE: this relates to rocket projectiles of volley fire systems. Rocket engine has body with relative elongation of more than 12 calibers and charge strongly connected with body and made in the form of two half-charges. Tail half-charge is made with tapered axial passage which widens towards nozzle, taper angle being equal to 0,05-0.5 deg. Head half-charge is made with star-shaped passage in which distance from top of star arm to body is equal to 0.75-0.9 of thickness of initial firing dome as average in length of tail half-charge. Relative elongation of half-charges is determined as equal to 6-6.5 of internal diameter of body. Aforesaid embodiment of engine allows for reducing period of final burning of charge with simultaneous enhancing stability of process. EFFECT: higher efficiency. 1 dwg

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RU 2 125 175 C1

Authors

Obozov L.I.

Kashirkin A.A.

Peturkin D.M.

Semilet V.V.

Makarovets N.A.

Kutsenko G.V.

Nekrasov V.I.

Shevrikuko I.D.

Amarantov G.N.

Smirnov V.D.

Kuz'Mitskij G.Eh.

Vronskij N.M.

Lisovskij V.M.

Grinberg S.I.

Makarov L.B.

Filatov V.G.

Dates

1999-01-20—Published

1998-02-20—Filed

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