SOLID-PROPELLANT ROCKET ENGINE WITH TURNING CONTROL NOZZLE (VERSIONS) Russian patent published in 2011 - IPC F02K9/28 F02K9/32 F02K9/84 

FIELD: engines and pumps.

SUBSTANCE: solid-propellant rocket engine includes combustion chamber and hidden turning control nozzle with thermal-protective coating, which is attached to it. Charge consists of two parts separated with partition; at that, larger part of the charge, which is located between front bottom and partition, is made from high-temperature propellant, and smaller charge part, which is located above hidden part of the nozzle, is made from low-temperature slow-burning propellant. Smaller charge part has shaped surface providing the flow of combustion products, which is close to constant flow. As per one of the versions of rocket engine the partition is made in the form of disc with flanging along central hole in it. Inner surface of flanging encloses the front point of nozzle so that annular gap the value of which remains constant during turning of the nozzle is provided. As per another version, between partition and nozzle, on inlet part of nozzle, on ribs there installed is the ring the inner surface of which encloses the front point of nozzle with the gap the size of which remains constant during nozzle turning. Outer surface of ring has spherical shape with the centre coinciding with centre of rotation of the turning nozzle and forms a spherical hinge together with partition.

EFFECT: invention allows reliable and stable thermal protection of rocket engine nozzle and reduction of weight of the latter.

5 cl, 2 dwg