Guidance devices

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

Patent

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Details

F42B 1518

Patent

active

041935675

ABSTRACT:
1. A guidance system mounted on a projectile comprising first and second sections mounted on the projectile to rotate about the longitudinal axis thereof, means for rotating said first section when the projectile is in flight, sensor means including a part removed from the longitudinal axis of the projectile rotatable with said first section for receiving emanation from a target and emitting a signal pulse in response thereto when the said part is facing the target and the longitudinal axis of the projectile and the target lie in a straght line, means including said second section for applying a steering force to the projectile at a point rotatable with said second section and directed perpendicularly to the longitudinal axis of the missile, means for rotating said second section when the projectile is in flight, means for generating a position pulse when said first and second sections are in such relation that the steering force tends to steer the missile in the direction in which said part is facing and means responsive to coincidence of said signal and position pulses for deactivating said means for rotating said second section.

REFERENCES:
patent: 2822755 (1958-02-01), Edwards et al.
patent: 2935942 (1960-05-01), Young et al.
patent: 2974594 (1961-03-01), Boehm
patent: 3072055 (1963-01-01), Ross

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