SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2007 - IPC F02K9/36 

FIELD: rocketry.

SUBSTANCE: proposed solid-propellant rocket engine contains combustion chamber with channel charge placed inside burning over surface and channel, and igniter installed at front end plate of engine. Conical bushing made of noncombustible material and tightly glue into charge channel is connected with front end plate of engine. Area of front end face of propellant charge is made with due account of relationship protected by present invention. Angle of cone of bushing glued into charge channel is within 5° and 10°. Igniter is separated from charge by rigid screen-cap connected to front end plate of engine with peripheral flanging to side of front end face of charge. Fixing of charge in engine is made with displacement of front end face of charge inwards screen-cap towards front end plate with provision of clearances between-cap, combustion chamber and charge.

EFFECT: relieving of solid propellant grain from tear off stresses of glued-in bushing, provision of guaranteed ignition of high-elongation solid-propellant charge with exclusion of action of gas dynamic pressure wave from igniter combustion product onto front end face solid propellant grain.

6 cl, 6 dwg