Missile homing device

Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance

Patent

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Details

244 313, F41G 726, F42B 1501

Patent

active

050822012

ABSTRACT:
The disclosed device can be used to determine coordinates expressing the angular deviation between the direction in which a missile is located and a line of sight in which a target is located. The device comprises means to project and shift an image on a linear senor, in such a way that the field of acquisition of the homing device has a section, by a plane perpendicular to the line of sight, that is ring-shaped having a diameter corresponding to a wide field aperture at the moment when the missile is launched, so that the missile is definitely intercepted in the field of acquisition, and then having a diameter that is variable as a function of time in such a way that the ring follows the missile as and when it approaches the line of sight through the action of a remote control system or a directive beam system. Finally, the section of the field is reduced to a simple disk, corresponding to a field having a very small angular aperture, giving a better range than standard homing devices and giving a low probability of false alarms arising out of the presence of the sun or of decoys. The device can be applied to weapons systems.

REFERENCES:
patent: 3912859 (1975-10-01), Christopherson
patent: 4193688 (1980-03-01), Watkins
patent: 4227077 (1980-10-01), Hopson et al.
patent: 4236177 (1980-11-01), Oshima et al.
patent: 4243187 (1981-01-01), Esker
patent: 4383663 (1983-05-01), Nichols
patent: 4393408 (1983-07-01), Beck et al.
patent: 4423437 (1983-07-01), Beck et al.
patent: 4476494 (1984-10-01), Tugaye 244 3.17

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