Polaris guidance system

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

Patent

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Details

244 322, F41G 736, F42B 1518

Patent

active

044705620

ABSTRACT:
An inertial guidance system for a rocket powered ballistic missile which vides navigation and control while the missile is proceeding in its flight trajectory. Signals are generated within the confines of the missile and without outside information representative of angular and linear motion of the missile with respect to an inertial frame of reference, a digital computer compares these signals against a preset parameter stored in the computer to provide control signals along the pitch and yaw axes. An autopilot uses these control signals to provide mechanical control movements, and an exhaust nozzle deflection arrangement connected to the autopilot deflects the exhaust of the rocket for guidance along a predetermined flight trajectory.

REFERENCES:
patent: 2946539 (1960-07-01), Fischel
patent: 3003312 (1961-10-01), Jewell
patent: 3078042 (1963-02-01), Grado
patent: 3164340 (1965-01-01), Slater et al.
patent: 3219293 (1965-11-01), Parker et al.
patent: 3231726 (1966-01-01), Williamson
patent: 3249324 (1966-05-01), Coffman
patent: 3301508 (1967-01-01), Yamron

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