Missile guidance system utilizing polarization

Aeronautics and astronautics – Missile stabilization or trajectory control – Remote control

Patent

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Details

244 314, 356152, F42B 1500

Patent

active

040970078

ABSTRACT:
A missile guidance system in which a projectile or missile is fired toward predetermined target with the missile being tracked on its flight toward the target by radar, processing the radar information in a computer apparatus and finally computing a new trajectory from the missile to the target and transmitting correction signals to a correction device on the missile including thrusters on the missile to cause the trajectory of the missile to be changed to the newly computed trajectory for the missile. This system corrects the trajectory of the missile while in flight by recomputing a trajectory from the missile to the predetermined target and making appropriate corrections each time. Thisenables the missile to only contain radar reflecting means, and correction detection and control means on the missile rather than having gyro and other type devices on board the missile which take up a considerable amount of space and weight.

REFERENCES:
patent: 3374967 (1968-03-01), Plumley
patent: 3603686 (1971-09-01), Paine
patent: 3698811 (1972-10-01), Weil
patent: 3848830 (1974-11-01), Born
patent: 3899145 (1975-08-01), Stephenson
patent: 3995792 (1976-12-01), Otto, et al.

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