POLARIS GUIDANCE SYSTEM
Assignee
Filed
Oct 22, 1965
Granted
Sep 11, 1984
Location
WOLLASTON MA US
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.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Mar 3, 1982
Rescinded
Feb 23, 1984
Duration
1 year, 11 months
Inventor
- 1ELDON C. HALL
Technology Domains
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Record Details
- Patent number
- US 4470562
- Application
- 04502717
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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