Body fixed terminal guidance system for a missile

Details Body fixed terminal guidance system for a missile Body fixed terminal guidance system for a missile

1997-06-13

1998-12-15

Jordan, Charles

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

F41G 700

Patent

active

058487646

ABSTRACT:
A guidance system (30) for a missile comprising a sensor (20) mounted on the missile and having a fixed line-of-sight relative thereto. The body fixed sensor (20) provides a first signal representing frames of image data. A processor (40) identifies a target in the frames of image data and provides a second signal representative of the location of the centroid thereof. A conventional tracker (36) follows the target and provides a third signal representative of an aim point of the missile. A controller (44) then changes the velocity vector of the missile in response to the second and third signals. In a specific embodiment, the body fixed sensor (20) provides first and second frames of image data. The system (32, 34) subtracts the first and second frames of image data and ascertains a growth center of the target. The processor (40) compares the image growth center to the aim point and provides an error signal in response thereto. The controller (44) then changes the velocity vector of the missile as necessary to maintain the error signal within a predetermined value. The processor (40) also provides an estimate of missile travel time to the target. When the travel time to target drops below a predetermined threshold, terminal guidance is effected by an inertial measurement unit (46).

REFERENCES:
patent: 3964695 (1976-06-01), Harris
patent: 4383663 (1983-05-01), Nichols
patent: 4898341 (1990-02-01), Terzian
patent: 5211356 (1993-05-01), McWilliams et al.
patent: 5303878 (1994-04-01), McWilliams et al.
patent: 5341142 (1994-08-01), Reis et al.
patent: 5435503 (1995-07-01), Johnson, Jr. et al.

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