METHOD OF MISSILE RADAR-BEAM-CONTROL GUIDANCE AND DEVICE TO THIS END Russian patent published in 2012 - IPC F41G7/00 F42B15/01 

FIELD: weapons and ammunition.

SUBSTANCE: set of inventions relates to weapons, particularly, to guided missiles with homing heads (HH). In missile guidance the following jobs are executed: generation of signals for control over radar beam for elevation and horizontal plane, reception of missile radio teller boresight signals, determination of coordinates and generation of missile control signals proportional to missile linear deviations from preset radar beam axis position, transmission of control signals to missile radio receiver, injection of missile into homing head lock-in zone, changing from radio command mode to homing mode, independent search, identification, lock-in and tracking. In generation of radar beam and missile control commands proceeding from possible calculated flight paths and rocket path position parameters, missile path is selected whereat (β_max-β_min)<β_0.5, where β_max and β_min are maximum and minimum calculated angles of mismatch between missile lengthwise axis in flight and ''radar-missile'' axis, β_0.5 is missile antenna beam width, angle between points of diagram half power. Missile homing system exploits command station radar and surface control hardware with clocking and coding unit. Missile incorporates homing head, command switch, control hardware and actuator to control missile airframe course and pitch angles, as well as radio teller, radio receiver and control command decoder. Additionally, missile incorporates forced rolling assembly mounted on missile airframe. Axes of radio teller and radio receiver antenna diagram are turned with respect to missile lengthwise axis through angle β_turn ⁼(β_max+β_min)/2.

EFFECT: reliable operation.

2 cl, 2 dwg