SOLID-FUEL MISSILE Russian patent published in 2013 - IPC F42B15/00 B64G1/40 F02K7/18 

FIELD: weapons and ammunition.

SUBSTANCE: solid-fuel missile comprises a start engine of I stage with a powder pressure accumulator of stages separation, a forward-flow rocket engine of II stage with a nozzle and an air duct, in the afterburning chamber of which there is a start engine installed with loose fit in series with a solid fuel gas generator. The solid fuel missile is equipped with a motor of III stage, with its nozzle bottom sunk into the afterburning chamber of the forward-flow engine and joined connection compartment. Around the front bottom of the start engine and the nozzle bottom of the engine of III stage there are power structures installed, which are rigidly fixed in flanges of the connection compartment and the front bottom of the start engine. Between the flanges there is a transition cylindrical spacer, which is rigidly connected with the power structure installed on the start engine, and resting with a free end to the power structure of the engine of the III stage. On the inner surface of the afterburning chamber there i an afterburning chamber nozzle installed with loose fit and equipped with a fixator of final position on the end cut of the afterburning chamber, and is fixed with a rupture joint on the front bottom or the appropriate power structure of the start engine. The gas generator body is made in the form of a hollow cylinder covering the cylindrical insert and installed with a circular gap between the inner surface of the afterburning chamber. The air ducts are arranged along the perimeter of the afterburning chamber between the nozzle bottom of the engine of III stage and the gas generator. Between flanges of the nozzle bottom of the engine of III stage and the flange of the connection compartment there is a rupture link.

EFFECT: increased distance of missile flight.

3 cl, 5 dwg