Line of sight missile guidance

Details Line of sight missile guidance Line of sight missile guidance

1986-10-31

1988-06-14

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Remote control

244 315, F41G 720

Patent

active

047506881

ABSTRACT:
In known guidance systems, the missile is guided by a control loop which includes the missile and a ground-based tracker, the tracker determining the relative positions of the missile and target and hence the lateral acceleration to be applied to the missile. However, these systems do not take account of the lateral acceleration generated by the coupling of the missile acceleration along its longitudinal axis and the angle between the body of the missile and the sightline, as in cases where acceleration is small the effect is insignificant. Described herein is a system for modifying the demand component to effect compensation for the lateral acceleration component imparted to the missile by virtue of its angle of incidence. This is accomplished by modifying the demand component in accordance with a stored predetermined time-varying gain term thereby to effect compensation of the lateral acceleration component imparted to the missile by virtue of the angle of incidence of the missile.

REFERENCES:
patent: 4465249 (1984-08-01), Selince
patent: 4492352 (1985-01-01), Yueh
patent: 4529151 (1985-07-01), Skarman
patent: 4541591 (1985-09-01), Chadwick et al.

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