Accession Number : ADD011324

Title :   Polaris Guidance System.

Descriptive Note : Patent,


Personal Author(s) : Hall,E C ; Sabo,J D ; Forter,S A ; Ragan,R R ; Laning,J H

Report Date : 11 Sep 1984

Pagination or Media Count : 55

Abstract : This patent discloses a inertial guidance system for a rocket powered ballistic missile which provides 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 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 and 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.

Descriptors :   *Patents, *Inertial guidance, *Guidance computers, *Guided missile computers, Underwater to surface missiles, Digital computers, navigation reference, Automatic pilots, Exhaust nozzles, Deflection

Subject Categories : Guided Missile Traj, Accuracy and Ballistics
      Underwater-launched Guided Missiles

Distribution Statement : APPROVED FOR PUBLIC RELEASE