Abstract: A guidance seeker system for a projectile includes a plurality of photoconductive sensing elements symmetrically disposed about a central axis of the projectile. When a target is illuminated with a light source, a lens transmits light reflected from the target to one or more of the photoconductive sensing elements. Dependent on which photoconductive sensing element is irradiated, a variance between the line of flight of the projectile and the target is determined. A voltage impulse resulting from irradiation of the photoconductive sensing element triggers actuation of a course corrector, such as a diverter, to nudge the line of flight of the projectile to increase the likelihood of the projectile reaching the desired target. This guidance seeking system is particularly effective when the target is designated with a pulsed laser.

Abstract: A guidance seeker system for a projectile includes a plurality of photoconductive sensing elements symmetrically disposed about a central axis of the projectile. When a target is illuminated with a light source, a lens transmits light reflected from the target to one or more of the photoconductive sensing elements. Dependent on which photoconductive sensing element is irradiated, a variance between the line of flight of the projectile and the target is determined. A voltage impulse resulting from irradiation of the photoconductive sensing element triggers actuation of a course corrector, such as a diverter, to nudge the line of flight of the projectile to increase the likelihood of the projectile reaching the desired target. This guidance seeking system is particularly effective when the target is designated with a pulsed laser.

Abstract: A missile guidance system utilizing a single microwave radiometric sensor for both terrain correlation and target homing. Terrain correlation is used to get the missile within the acquisition range of the homing system, and the homing system is used in the terminal phase of operation.

Abstract: A method for guiding an intercepting missile to a body-to-body contact with an airborne target in the atmosphere. The method includes the steps of guiding the intercepting missile to within an appropriate distance from the airborne target, illuminating the airborne target, using an illuminator carried by the intercepting missile, acquiring an image of the illuminated airborne target and, steering the missile in accordance with an aimpoint on the image.

Abstract: A system for guiding projectiles to a target. More particularly, a system for the guidance of projectiles toward a target using a photo detector array (18) and an arrangement of single use thrusters (22). The system is capable of guiding projectile to targets after firing from extended distances.

Abstract: A missile system and method for performing automatic fire control in which a reconnaissance vehicle is used to gather video reference information of a target and this information is then communicated to a launching vehicle from which missiles are caused to be trained on the selected target by utilizing an automatic target handoff correlator that identifies the selected target, causes an autotracker to be locked on and finally a computer is signaled by the automatic target handoff correlator to cause a missile to be fired.

Abstract: A fire control system for a short range guided missile in which the system is contained on a vehicle such as a track vehicle that can be easily camouflaged from the enemy and including video means for acquiring a target desired to be destroyed and utilizing this video information as reference information in an automatic target handoff correlator which correlates the reference information from video signals from a missile that was launched from the vehicle and guided by a missile control computer to the field of view of the selected target with the automatic target handoff correlator comparing the reference video signals and the seeker video signals from the missile to place the target in the center of the field of view of the seeker and once this is done a missile autotracker is commanded to lock-on and guide the missile to the selected target.

Abstract: An optical system includes a nonspherical outer dome that is rotationally symmetric about a central axis, a detector system, and an optical corrector positioned in an optical path between the outer dome and the detector system. At least one light baffle is positioned in the optical path between the outer dome and the detector system and is fixed in space relative to the central axis. There are typically from one to three baffles, each affixed to either the inter surface of the outer dome or to the optical corrector. Each baffle is a frustoconical tube that is rotationally symmetric about the central axis. A set of fins may be supported on one of the baffles, with each fin extending radially outwardly from an outer surface of the baffle and parallel to the central axis. The baffles combine to reduce stray light that otherwise would enter the optical system.

Abstract: The invention relates to a method for combating near-surface and/or surface targets such as tanks or the like by using a missile comprising a seeker head, an effective charge and at least one thruster. According to the invention, the missile is redirected into an essentially horizontal cruising and seeking phase after completing an essentially vertical start phase. During said cruising and seeking phase, the missile scans the terrain ahead of it using the seeking head, whereupon an approaching phase which is directed in an essentially downward direction follows after the finally ensues head locks onto an identified target. An external reconnaissance system in an appropriate aircraft and/or spacecraft such as in a helicopter, a drone or in a satellite receives information for guiding the missile which is transmitted to the same.

Abstract: A guidance seeker system for a projectile includes a plurality of photoconductive sensing elements symmetrically disposed about a central axis of the projectile. When a target is illuminated with a light source, a lens transmits light reflected from the target to one or more of the photoconductive sensing elements. Dependent on which photoconductive sensing element is irradiated, a variance between the line of flight of the projectile and the target is determined. A voltage impulse resulting from irradiation of the photoconductive sensing element triggers actuation of a course corrector, such as a diverter, to nudge the line of flight of the projectile to increase the likelihood of the projectile reaching the desired target. This guidance seeking system is particularly effective when the target is designated with a pulsed laser.

Abstract: A method to determine the direction in which a spinning projectile is traveling. A solar sensor array on the projectile is used to calculate the orientation of the axis of rotation of the projectile with respect to a known solar field and a magnetometer sensor array is used to calculate the orientation of the axis of rotation of the projectile with respect to a known magnetic field, both fields being represented by respective vectors having magnitude and direction. With the known and calculated orientations, the pointing direction may be obtained by vector combination.

Abstract: The present invention relates to a system for sweeping a laser beam in a preset pattern, while, at the same time, directing the pattern to any area in a predetermined scanning area. The invention is particularly useful in LADAR applications. In one version of the invention, a series of optical prisms are arranged in concentric tubes so that the prisms have a common optical path. The tubes and, hence, the prisms, may be independently rotated by precision electric motors coupled to gear rings on the tubes.

Abstract: An optical system includes a window, an optical corrector formed of a curved piece of a transparent material having a front surface and a back surface, and a sensor system with a sensor positioned such that the optical corrector is between the window and the sensor. At least one of the front surface and the back surface of the optical corrector is a segment of a convex aspheric curve rotated about a center, otherwise known as a torus.

Abstract: The Multispectral-Hyperspectral Sensing System (MHSS) comprises a control center, a surveillance platform and at least one weapon battery with known sensing and destroying capabilities. The control center has access to pre-existing information relating to the target scene and potential targets, although not necessarily current, as well as the capabilities and limitations of the available weapons. This pre-existing information is communicated to the surveillance platform to be used in collecting hyperspectral/multispectral image data of the target scenery and to derive from the collected image data the relevant current target data subset. The derived data subset is then down-linked to the control center, which performs further processing to make it useful to the selected weapon. The weapon receives the target signature update from the control center and, in response, performs a significantly more precise strike at the selected target than based just on the a priori knowledge base.

Abstract: An optical system includes a curved window, an optical corrector adjacent to a curved inner surface of the window, an optical train positioned such that the optical corrector lies between the curved window and the optical train, a movable optical train support upon which the optical train is mounted, and a sensor disposed to receive an optical ray passing sequentially through the window, the optical corrector, and the optical train. The optical corrector has an inner surface and an outer surface, at least one of which has a shape described by a modified Zernike polynomial surface.

Abstract: An optical system includes a curved window, an asymmetric, scoop-shaped optical corrector adjacent to a curved inner surface of the window, an optical train positioned such that the optical corrector lies between the curved window and the optical train, a movable optical train support upon which the optical train is mounted, and a sensor disposed to receive an optical ray passing sequentially through the window, the optical corrector, and the optical train. The optical corrector has an inner surface and an outer surface, at least one of which has a shape defined by an asymmetric polynomial.

Abstract: One aspect of the invention relates to a laser ranging system.

Abstract: In missile guidance systems, knowledge of the target's flight policy and doctrine, along with an analysis of local topographic features, are used in a minimum commitment guidance policy. By assuming certain objectives of the target, paths may be defined by evaluating the degree of detection avoidance provided by the terrain adjacent to the various paths. To maximize the probability of intercept, a missile may be guided in a direction covering the most likely of these paths for periods while the target is hidden. The paths are then reevaluated each time the target is detected. For highly maneuverable targets that are capable of executing violent changes in direction and speed, the topography-aided guidance system maximizes the probability that the target can escape the missile intercept envelope.

Abstract: A large (10's of meters) aperture space telescope including two separate spacecraft—an optical primary objective lens functioning as a magnifying glass and an optical secondary functioning as an eyepiece. The spacecraft are spaced up to several kilometers apart with the eyepiece directly behind the magnifying glass “aiming” at an intended target with their relative orientation determining the optical axis of the telescope and hence the targets being observed. The objective lens includes a very large-aperture, very-thin-membrane, diffractive lens, e.g., a Fresnel lens, which intercepts incoming light over its full aperture and focuses it towards the eyepiece. The eyepiece has a much smaller, meter-scale aperture and is designed to move along the focal surface of the objective lens, gathering up the incoming light and converting it to high quality images.

Abstract: An infrared seeker head for target tracking missiles has a main detector and an imaging optical system generating an image of a field of view on the main detector. The field of view contains a target such as an enemy aircraft. The missile is guided to the target in accordance with signals from the main detector. The target, if attacked by the missile, emits high-intensity laser radiation towards the missile as a counter-measure. This is to disturb the operation of the seeker head by dazzling or even destroying the main detector. The seeker head contains a device for defending against such disturbances. Various types of such defending devices are described. Incident light is deviated from the main detector. A second-quadrant-detector of reduced sensitivity guides the missile along the disturbing laser beam. Another embodiment uses attenuating optical elements in front of the main detector under the control of one or more second detectors.

Abstract: An optical system includes a window made of a curved piece of a transparent material having an inner surface and an outer surface. The inner surface has a nominal inner surface shape defined by a first conicoidal relationship, and the outer surface has a nominal general aspheric surface shape. The optical system also typically includes a sensor and an optical train on the side of the inner surface of the window. The accuracy of the shape of the inner surface is tested by directing a coherent light beam through a remote focus of the inner surface, reflecting the light beam from the inner surface toward an adjacent focus of the inner surface, reflecting the light beam from a spherical reflector at the adjacent focus of the inner surface and back toward the inner surface, reflecting the light beam from the inner surface back toward the remote focus, and interferometrically comparing the reflected beam arriving at the remote focus with a reference beam.