SOLID PROPELLANT ROCKET ENGINE Russian patent published in 2012 - IPC F02K9/08 F02K9/30 

FIELD: engines and pumps.

SUBSTANCE: solid propellant rocket engine comprises a body coupled with a bulkhead connecting a body to a spherical receiver by means of a response bulkhead, the receiver is equipped with four nozzle flanges, four nozzles fixed to nozzle flanges, a charge and an igniter. Axes of nozzles are made at the angle to the longitudinal axis of a solid propellant rocket engine, and axes of nozzle flanges are made at the angle making 0.2…0.7 of the angle of nozzle axes inclination, relative to the perpendicular line to the longitudinal axis of the solid propellant rocket engine. The charge comprises two half-charges having central channels and tightly fixed to the receiver and the body, accordingly. The value of the half-charge burning arch tightly fixed to the receiver is equal to the difference between the inner radius of the receiver and the inner radius of the response bulkhead. The half-charge tightly fixed to the receiver has slots connecting a central channel with holes in nozzle flanges.

EFFECT: invention makes it possible to reduce structure weight and dimensions of a solid propellant rocket engine, and also to reduce losses of a specific thrust pulse.

2 cl, 1 dwg