A sight system for guiding a missile towards a moving target by use of a guidance beam that can be used for the missile to trail the target. A first viewing device receives visible light and/or a second viewing device receives non-visible light radiating from the target. The viewing device(s) include adjustable alignment marks being aligned by use of a light source and a guidance beam detector arranged together in one common position.

Device and method for a sight

A system for correcting the trajectory of a projectile so that it reaches a designated target. The system comprises an optical radar comprising a laser emitting in the infrared band that makes it possible, in association with a processing device, to follow the movements of the target and of the projectile at the same time. The pieces of information given by the processing device enable a computer to calculate corrections to be made to the trajectory of the projectile in a final stage so that it meets the target. By modifying the trajectory of a projectile, such as a self-propelled missile or a shell, launched towards a target, the projectile can be made to hit a moving target or pass by at a reasonable distance that is small enough for the explosion provoked by its charge to definitely destroy the target.

System to correct the trajectory of a projectile

This invention is a beam rider system and method that utilizes polarization-agile millimeter beams. Information is spatially encoded in the beams by varying the rate of rotation of the linearly polarized vector of the beams. In one embodiment, information is encoded on a beam that is nutated around a centerline flight path of a missile. In another embodiment, information is encoded on four parallel beams that form a centerline which is the intended flight path of the missile. Receiver means in the flying missile receive and decode information from the beams and use this decoded information to guide the missile to a target.

Missile beamrider guidance using polarization-agile beams

An infrared tracker for tracking a carrier in clutter comprises a pyrotechnically heated emitter, a beam concentrator, and a blanking means all of which are mounted on the carrier, and a command link, a thermal detector, a display signal storage means, a display, and a comparator all of which are located remotely to the carrier, said command link operative to provide an emitter start-up signal and a blanking command signal, said emitter and blanking means operative in response to the command signals sent to the carrier when there is clutter present that might be confused with the carrier, respectively, to actuate the emitter and blanking means, said display storage means operative to store a first video frame of the carrier while the emitter is blanked out, and said comparator for comparing the first video frame without the emitter to a subsequent video frame including the emitter to distinguish between the clutter and the carrier.

Carrier tracking system

A target intercept guidance system for directing a steerable object, such a torpedo with a guidance point. The guidance system is located at a launching vehicle and senses the bearings from the launching vehicle to a target and to the steerable object as it moves toward the target. Various error signals are then generated and classified into sensed linguistic variables using membership functions of corresponding sensed variable membership function sets based upon primary and secondary goals to become fuzzy inputs that produce fuzzy control output membership functions from a control output membership function set based upon logical manipulation of the fuzzy inputs. The control system performs this classification and selection according to sometimes competing goals of excluding the torpedo from a particular operating zone while guiding the torpedo in response to variations in a target bearing relative to the guidance point. The selected fuzzy control output membership functions are converted into an output having an appropriate form for control, subject to optional conditioning to prevent unwanted effects and assure good behavior for different tactical parameters.

Hierarchical target intercept fuzzy controller with forbidden zone

A guidance apparatus (10) for guiding a missile (18) to a target (20) by a beam (16) is disclosed. The apparatus (10) includes a device (12) for projecting the beam (16), the orientation of which controls the flight path of the missile (18). The missile (18) includes a circuit for generating a signal when the missile (18) is in a predetermined spatial relationship (e.g., the center coded portion) with respect to said beam (16). When such signal is generated, the angular position of the missile with respect to the target is determined. This positioned relationship is then provided to ground based circuitry (56, 58 and 60) which forms a part of apparatus (10) and which adjusts the orientation of the beam (16) to reduce the angular separation of missile and target.

Hans A. Maurer

Papers

Beamrider guidance system