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

FIELD: rocketry.

SUBSTANCE: the solid-propellant rocket engine has a body, charge, nozzle and an ignition device with a pyrotechnical component positioned in a perforated housing. The ignition device housing is made in the form of a woven sleeve formed by means of a tape of composite material with formation of delivery holes, whose total area makes up 0.3 to 0.5 of the area of the side surface. Rigidly installed inside the sleeve, on the side of the front bottom of the engine, is a hollow split bush with radial lugs on the inner surface, a weighed portion of pyrotechnical component is positioned in the cavity. A stepped piston is installed in the bottom of the sleeve, in its axis of symmetry. A compensator made of elastic material is installed on the piston with a stop at the end face of the pyrotechnical component enclosed in a destructable shell.

EFFECT: enhanced reliability of the solid-propellant rocket engine within a wide temperature range of operation due to excluded concentrated power action on the charge surface.

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