CRUISE MISSILE AND METHOD OF COMBAT USE THEREOF Russian patent published in 2020 - IPC F42B12/66 F42B15/00 

FIELD: weapons.

SUBSTANCE: group of inventions relates to missile weapons and, in particular, to guided missiles used for ground and surface targets. Cruise missile comprises body, wing with roll control elements, horizontal tail unit with rudder and vertical tail unit with rudder, power plant. Inside the body there installed is inertial navigation system, active radar head of self-guidance - ARS. There is a control system, an on-board computer, a system for separating combat elements from the missile body and at least one detachable combat element containing an engine, a warhead and a guidance system. Guidance system of each of the combat elements includes a memory unit, an inertial navigation system, a radio altimeter and a target coordinator. Combat elements are made in the form of small-size supersonic missiles with effective surface of reflection of each element smaller than effective surface of reflection of their carrying missile. Coordinator of each combat element target is made in the form of semi-active self-guidance head. Proposed invention relates to rocket armament, in particular to guided missiles used for ground and surface targets. Proposed invention relates to rocket armament, in particular to guided missiles used for ground and surface targets. Cruise missile hull is equipped with a target illumination station - TIS. It is tuned to the frequency of operation of semi-active homing heads of combat elements and is connected by electric connections with ARS, inertial navigation system and on-board computer. Body of cruise missile comprises compartments for transportation of combat elements with closing flaps and separation system. Proposed system comprises devices retaining combat elements inside combat element transportation compartments, device for opening and closing flaps of combat element transfer compartments and combat elements separation device. Design of cruise missile is made so that all internal components of missile body, wing console, horizontal tail unit with elevator are located so that removal of centre of mass of cruise missile from its centre of pressures in area of operational restrictions, at which stable flight of missile with combat elements, without combat elements, during separation and in time intervals between separate combat elements compartments is provided. This makes it possible, after separation of combat elements, to perform stable flight of the missile as a TIS carrier, and after illumination of the point of aiming the combat elements to perform flight as a false target.

EFFECT: technical result is higher accuracy of guidance of missile combat elements.

17 cl, 4 dwg