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

Abstract RU 2133369 C1

FIELD: rocketry. SUBSTANCE: engine includes powder charge whose channel is widened on side of front neck; start ands ignition device located in it at spaced relation has front head and cylindrical-spherical casing inside which support, igniter and perforated progressive-burning grain are located; support is made in form of cruciform bush with gas ducts changing into central critical orifice. head and casing of start and ignition device are provided with heat shields; electric igniter located in head opposite igniter is connected with start and ignition device by means of gas duct. Smooth heating accompanied by complete ignition of entire powder charge by jet of gas escaping from start and ignition device enhances operational reliability of rocket engine, both at positive and negative temperatures. EFFECT: enhanced efficiency of rocket engine. 2 dwg

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RU 2 133 369 C1

Authors

Shipunov A.G.

Sokolov G.F.

Morozov V.D.

Vasina E.A.

Makhonin V.V.

Dates

1999-07-20Published

1997-07-01Filed