A guidance assembly and method for guiding an ordnance to a target. The assembly can operated in navigation and targeting modes and has an imager/seeker including an objective lens assembly and an imaging sensor array which provide image data for mapping and terminal seeker performance. The imager/seeker is pivotally mounted on the ordnance. An actuator is coupled to the imager/seeker and can be actuated to pivot the imager/seeker relative to a longitudinal axis of the ordnance from a navigation position to a targeting position. A flight control unit communicates with the imager/seeker and the actuator, and has a processor which analyses the image data to provide navigation flight control signals for guiding the ordnance in the navigation mode of operation and determining a target direction via automatic target recognition or aimpoint algorithms for directing the ordnance to the target in the targeting mode of operation.

Methods and apparatus for variable time sampling of optical pulses by a unit cell are disclosed. The methods may include detecting whether an amplitude of an optical pulse incident on one or more photo-detecting elements exceeds a sampling threshold, and while the pulse amplitude remains above the sampling threshold, iteratively sampling the optical pulse at a sampling rate that varies based on changes in the pulse amplitude.

Methods and apparatus for variable time sampling of optical pulses by a unit cell are disclosed. The methods may include detecting whether an amplitude of an optical pulse incident on one or more photo-detecting elements exceeds a sampling threshold, and while the pulse amplitude remains above the sampling threshold, iteratively sampling the optical pulse at a sampling rate that varies based on changes in the pulse amplitude.

A guidance system for remote guidance of a remote platform(s) towards a target destination is disclosed. The guidance system includes a light module including a light source operable for beam to illuminating the remote platform, and a spatial light modulator (SLM) placed in the optical path of the light beam emitted from the light source. The guidance system includes a controller operable for obtaining data indicative of guidance information for navigating the remote platform towards the target destination. The controller operates the SLM to encode the guidance information in the light beam. The guidance information may be encoded in light pattern including at least one of the following: a spatial light pattern formed in a cross-section of the light beam, a temporal light pattern in the light beam, and a spatiotemporal light pattern. The guidance information is encoded in the light beam such that the remote platform can navigate towards the target by detecting at least a cross-sectional region of the light beam, decoding a portion of the guidance information encoded in the detected cross-sectional region and thereby determining guidance instructions for navigating the remote platform(s) towards the target destination.

A weapon and weapon system, and methods of manufacturing and operating the same. In one embodiment, the weapon includes a warhead including destructive elements and a guidance section with a seeker configured to guide the weapon to a target. The seeker includes a detector configured to receive a distorted signal impinging on an objective lens from the target, memory configured to store target criteria and a correction map, and a processor configured to provide a correction signal based on the distorted signal, the target criteria and the correction map to guide the weapon to the target.

Upon loss of a valid track of a remotely-sensed command guided vehicle, a delta actuator command including an orthogonal component orthogonal to the straight-line path is generated as a next sample of a time-based alternating signal. The time-based delta actuator command is added to the nominal actuator command, which is held upon loss of valid track, to maneuver the vehicle in first and second orthogonal directions back and forth across the straight-line path to increase an area of vehicle motion relative to the tracker's FOV. This increases the likelihood of recapture of the vehicle given vehicle motion after track is broken. The penalty is a reduction in energy efficiency. In certain embodiments, this is accomplished without modification to guidance system hardware or the existing tracking valid or invalid guidance algorithms.

A method for aligning a missile with a target in a laser beam riding missile guidance system, the system including a laser transmitter for generating and projecting a laser information field towards the target and an optical sight for aiming the laser beam towards the target, the method comprising: determining a point in the laser information field with which the missile is currently aligned; determining a distance of the target from the missile; determining an angular displacement between the missile's current direction of travel and the direction in which the target lies from the missile; determining, based on said distance and angular displacement, a new point in the laser information field with which the missile should be aligned to reach the target; and controlling missile guidance systems on board the missile to bring the missile into alignment with the new point in the laser information field.

A method for aligning a missile with a target in a laser beam riding missile guidance system, the system including a laser transmitter for generating and projecting a laser information field towards the target and an optical sight for aiming the laser beam towards the target, the method comprising: determining a point in the laser information field with which the missile is currently aligned; determining a distance of the target from the missile; determining an angular displacement between the missile's current direction of travel and the direction in which the target lies from the missile; determining, based on said distance and angular displacement, a new point in the laser information field with which the missile should be aligned to reach the target; and controlling missile guidance systems on board the missile to bring the missile into alignment with the new point in the laser information field.

The presently disclosed subject matter includes an active protection system and a method, dedicated for detecting, locating, and incapacitating beam-riding missiles and in that way protecting an asset from being targeted by the missile. According to some examples following receipt of a threat-indication, the active protection system estimates a location of a beam used for directing a threat (e.g., ATGM) to the target and launches an aerial platform that flies in the opposite direction along the beam until it meets and incapacitates the incoming threat.

An armored vehicle has a turret having a gun; a targeting system which is arranged inside the turret and is provided with a day channel, a night or thermal channel and a laser range-finder, a power control system for controlling the movement of the turret in azimuth and the movement of the gun in elevation; a device for guiding missiles using lasers, which generates a laser guiding line; and a turret controller which determines the mode for guiding the missile, wherein the turret has gyrostabilizer for gyrostabilizing the laser-guiding line.