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

Abstract RU 2125174 C1

FIELD: rocket engines. SUBSTANCE: this relates to rocket engines with charges of high-pulse mixed solid fuels strongly connected with body and they can be used in rockets (rocket projectiles) with hard-alloy engines with fuels which are liable to vibrating burning. Rocket engine has sectional charge of solid fuel and acoustic spaces located between sections of charge. Rear end-piece of slot-shaped (star-shaped) passage of front section is made with widening portion. Front end-piece of rear section passage is made with narrowing portion. Widening portion of front section is provided with cylindrical strip which is oriented in parallel to longitudinal axis of passage and it is located at side of rear end face of section in larger diameter of section. Made after narrowing portion of rear section is step preferably of toroidal configuration. Maximal diameter of narrowing portion of rear section passage is equal to 1.15-1.45 diameters of arms in front section passage. Depth of strip is 0.015-0.025, and its diameter is 0.5-0.7 of diameter of slots in front section. Height of step is 0.03-0.09 of difference between maximal diameter of narrowing section and passage proper in rear section of charge. Aforesaid embodiment of engine enhances stability of internal ballistic characteristics at wider spectrum of frequencies of suppressed oscillations. EFFECT: higher efficiency. 1 dwg

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RU 2 125 174 C1

Authors

Denezhkin G.A.

Semilet V.V.

Obozov L.I.

Borisov O.G.

Peturkin D.M.

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

1999-01-20Published

1998-02-20Filed