METHOD FOR ENTRY OF MISSILE INTO BEAM AREA AND COMPLEX OF MISSILE TELECONTROLLED IN BEAM FOR ITS REALIZATION (MODIFICATIONS) Russian patent published in 2005 - IPC

FIELD: armament, in particularly, rocketry, applicable in development of missile-weapon complexes with beam-rider guidance systems, in which the missile flight trajectory, for example, close to and parallel with the ground surface, or water surface.

SUBSTANCE: from the moment of start a program-changed pitch command is formed on the missile, and at an entry of the missile in the beam area control is effected by the TV guidance system. In the horizontal plane the directions of the missile start line and beam are matched with the zero value of command messages. In the vertical plane the direction of the missile start line is adjusted in angle above the beam direction with the zero values of the command messages, and the beam-rider guidance system is controlled by the guidance system from the moment of getting of the missile to the beam area with zero values of command messages in the vertical plane, the missile is twisted in bank angle. Described are two modifications of the complex of the missile telecontrolled in beam. The first modification has a missile that includes components of missile electromechanical joining, autopilot, and a series-connected receiver and a coordinate separation unit, as well as a control station that includes a sight-guidance instrument and a start control device, which is connected via the device of the electromechanical joining of the launcher to the components of the missile electromechanical joining, the receiver is coupled by electromagnetic radiation to the sight-guidance instrument; installed on the missile are a delay unit and series-connected starting pulse shaper, variable command shaper and an adder, the heading and pitch outputs of the coordinates separation unit are connected, respectively, to the first and second inputs of the delay unit, the heading output of the delay unit is connected to the first input of the autopilot, the pitch output of the delay unit is connected to the second input of the adder, the adder output is connected to the second input of the autopilot, and the third input of the delay unit is connected to the output of the starting pulse shape, whose input is connected to the components of the missile electromechanical joining. The second modification differs from the first one by the fact, that the receiver output is connected to the first input of the delay unit, whose output is connected to the input of the coordinates separation unit, the pitch output of the coordinates separation unit is connected to the output of the starting pulse shaper, whose input is connected to the components of the missile electromechanical joining.

EFFECT: enhanced efficiency.

4 cl, 6 dwg