SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2006 - IPC F02K9/95 

Abstract RU 2279564 C1

FIELD: rocketry; self-propelled missiles; volley fire systems.

SUBSTANCE: proposed solid-propellant rocket engine has housing, nozzle unit, igniter and electric igniter. Igniter and electric igniter are arranged in axial tube in supersonic part of nozzle unit. Plate and bushing connected with nozzle unit are secured on ends of axial tube. Bushing is connected with nozzle unit by stop with fixed shear force made in form of ring joint. Ring with axial hole is installed coaxially with axial tube in supersonic part of nozzle unit by means of easily detachable glue joint. Diameter of axial hole of ring is 1.1-1.2 of outer diameter of axial tube.

EFFECT: reduced spread of characteristics of solid-propellant rocket engine during ignition period.

1 dwg

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RU 2 279 564 C1

Authors

Akel'Ev Aleksandr Ivanovich

Belobragin Boris Andreevich

Kaljuzhnyj Gennadij Vasil'Evich

Kashirkin Aleksandr Aleksandrovich

Koroleva Natal'Ja Borisovna

Semilet Viktor Vasil'Evich

Denezhkin Gennadij Alekseevich

Makarovets Nikolaj Aleksandrovich

Tregubov Viktor Ivanovich

Dates

2006-07-10Published

2005-06-23Filed