Highly accurate long range optically-aided inertially guided typ

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

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244 311, 244 314, 244 315, 244 319, F41G 730, F42B 1501

Patent

active

061424129

ABSTRACT:
An optically-aided, inertially guided missile. The inventive missile includes a receiver for accepting guidance commands from a source located on an independent frame of reference relative to the missile and providing a first signal in response thereto. A filter is mounted on the missile for processing the first signal and providing a second signal in response thereto. The filter outputs commands to a navigation system which provides missile guidance commands in a conventional manner. In the illustrative implementation, the filter is a Kalman filter configured to eliminate the effects of gunner jitter and optical guidance system noise thereby significantly improving missile terminal performance at long ranges. In the illustrative implementation, the navigation system includes an inertial sensor assembly. The navigation system outputs a signal representative of missile-to-target cross track position and velocity in response to outputs from the sensor assembly and the filter. A guidance law is used by the system to compute missile acceleration commands in response to the missile-to-target cross track position and velocity. Thereafter, fin control commands are generated by an autopilot in response to the missile acceleration commands in a conventional manner.

REFERENCES:
patent: 3631485 (1971-12-01), Beazell, Jr.
patent: 3796396 (1974-03-01), Crovella
patent: 3964695 (1976-06-01), Harris
patent: 5308022 (1994-05-01), Cronkhite et al.

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