METHOD FOR GUIDANCE OF TELECONTROLLED MISSILE Russian patent published in 2004 - IPC

FIELD: rocketry, applicable in armament complexes of telecontrolled missiles.

SUBSTANCE: the method includes formation of wide and narrow control fields, missile launching at an angle to the target sighting line with a subsequent matching with it, missile acceleration with the aid of the engine, guidance of the missile in the wide control field in accordance with the attitude of the heat radiation source, on the missile, separation of the missile engine at its entry in the narrow control field and guidance of the missile in the narrow control field in accordance with the attitude of the missile radiation source. The novelty of the method for guidance is in the fact that missile guidance in the inclined plane from the launch moment is accomplished with an angular displacement of the missile relative to the target sighting line, the value of the angle of missile displacement is formed proportionally to the expected maximum angular dimension of the dust-smoke cloud, the directions of the angle of missile displacement and the missile launch angle relative to the target sighting line in the course plane are formed in accordance with the function sign, which takes into account the angular velocity of the target sighting line in the course plane, expected range of termination of the missile acceleration leg, cross-stream component of the wind velocity relative to the target sighting line, and matching of the missile with the target sighting line is performed from the moment of beginning of missile guidance in the narrow control field in accordance with the mathematical dependence, which takes into account the angle of missile displacement relative to the target sighting line, current time from the moment of beginning of missile matching, supposed time to the impact with the target from the moment of beginning of missile matching.

EFFECT: prevented overlap of the " carrier-missile", "carrier-target" optical communication lines by the smoke plume of the own acceleration engine of the missile and the dust-smoke cloud formed at a touchdown of the separated acceleration engine of the missile.

2 dwg, 1 tbl