SOLID FUEL ROCKET ENGINE Russian patent published in 2017 - IPC F02K9/28 

FIELD: engines and pumps.

SUBSTANCE: solid fuel rocket engine contains two casing halves, front and rear, equipped with front and rear end-burning half-charges, the open face ends of which face each other, and a nozzle cluster and ignitor which are gas-connected with the casing halves. The nozzle cluster is made as a single central nozzle gas-connected to the face ends of the half-charges via a flow pipe running through the rear half-charge. The rear half-charge is separated from the flow pipe which runs inside an armoured channel in the rear half-charge. The central nozzle is installed on a mounting flange which is on the rear casing half.

EFFECT: invention allows decreasing the engine transverse dimensions, increasing the total burn, avoiding thermal effect on the rear casing half, simplifying the structure of the engine and improving its design for manufacturability.

7 cl, 1 dwg