INTERCEPTOR MISSILE Russian patent published in 2024 - IPC F42B15/00 

FIELD: weapons.

SUBSTANCE: invention relates to armament, namely to interceptor missile. Interceptor jet comprises a multistage solid-propellant rocket engine consisting of a plurality of working chambers arranged along a common axis, docked to each other due to the fact that the upper part of the combustion chamber of the previous stage is tightly adjacent to the inner surface of the supercritical part of the nozzle of the next stage. At the edge of the supercritical part of the nozzle of the working chamber of each stage there are at least three cutouts, they are distributed along the nozzle circumference and covered with steering gates arranged on the outer side of the nozzle shell, which are fixed on the nozzle shell by means of a hinge located in the upper part of the damper and providing the possibility of controlled deflection of the damper to the outside. There is also a drive for deflection of said flaps by means of motion transmission mechanisms acting synchronously on flaps of all stages located on the common vertical line and not preventing free undocking of the stages. Steering flaps of all rocket stages of the multistage engine, located on one vertical line, are connected to each other by a chain consisting of levers performing the function of limiters of the value of possible opening of the flaps, and wire rods connecting said levers to each other, as well as to servo electric drive located on upper stage. Links of said chain belonging to adjacent rocket stages are connected by means of two levers connected to each other by means of a fork with an open slot oriented longitudinally relative to the rocket axis and located on arms of said levers moving transversely. Plane of rotation of the levers performing the function of the shutter opening limiter is located in relation to the shutter surface at an angle greater than the friction angle. Steering flaps located at least on one of the verticals are attached to the nozzle surface by means of a biaxial ball hinge, that is with possibility of deflection by angle not only in plane passing through rocket axis, but also in the plane transverse to the rocket axis, and they are connected to two independent servo electric drives acting on the corresponding two edges of one shutter.

EFFECT: possibility to control thrust vector direction during the whole rocket flight.

1 cl, 6 dwg