Method of guiding missiles

Details Method of guiding missiles Method of guiding missiles

1988-10-12

1990-02-06

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

244 317, F41G 722

Patent

active

048983411

ABSTRACT:
A method of guiding a missle during the terminal phase of an intercept. Images, successively formed as the missile approaches the target areas, are represented by a set of vectors. As the missile approaches the target, the image of the target appears to grow larger, and an estimate of the growth is computed. One vector is selected as an aim point, and the missile is guided towards that point. In one embodiment, well-suited for use on small targets, a vector is also selected as a track point, and the distance between the aim point and the track point is computed. The seeker head is controlled to keep the track point in the image and the aim point is located by multiplying the distance between the track point and the aim point by the growth factor. In a second embodiment, well-suited for use with large targets, a track point is selected very near the aim point. As the image grows so that the aim point and track point cannot both be in the field of view, a new track point is selected.

REFERENCES:
patent: 3416752 (1968-12-01), Hembree
patent: 3586770 (1971-06-01), Bonebreak et al.
patent: 3955046 (1976-05-01), Ingham et al.
patent: 4133004 (1979-01-01), Fitts
patent: 4162775 (1979-07-01), Voles

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