SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2005 - IPC

Abstract RU 2258151 C1

FIELD: rocketry.

SUBSTANCE: proposed solid-propellant rocket engine contains housing with channel charge, charge fitted in channel and igniter including housing with one of several nozzles-holes. Exit section of nozzle-hole of igniter is located at distance equal to 2-8 equivalent diameters of nozzle-hole from ignited surface of charge. Angle of tilting of axis of nozzle-hole to ignited surface is not less than 45°.

EFFECT: reduced mass of igniting composition required for operation of engine.

2 dwg

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RU 2 258 151 C1

Authors

Talalaev A.P.

Makarovets N.A.

Kuz'Mitskij G.Eh.

Kolesnikov V.I.

Amarantov G.N.

Baranov G.N.

Shamraev V.Ja.

Kolach P.K.

Samokhin V.S.

Mel'Nichenko M.V.

Beklemysheva T.M.

Fedchenko N.N.

Vronskij N.M.

Denezhkin G.A.

Podchufarov V.I.

Kuksenko A.F.

Sopikov D.V.

Bytskevich V.M.

Gramenitskij M.D.

Volkov O.K.

Dates

2005-08-10Published

2003-12-30Filed