Abstract: A Radar Counter Measure System (RCMS) and method for operating a decoy as a Radar Counter Measure (RCM) against incoming airborne threats, wherein the RCMS consists of an airborne vehicle (6) carrying a payload (8) launched from a platform (2) by a launcher (4). The payload contains one or more decoys. Each decoy includes a folded corner reflector construction (CRC) (14) which is released at a predetermined point on the vehicle's trajectory. The vehicle is launched by a gun (26), a mortar (20), a rocket (32) or another airborne device. Once released, the decoy is deployed and self-erected to become effective as a RCM. The self-erection mechanism (12) is mechanical, pneumatic, pyrotechnic or aerodynamic. The payload (8) may hold various kinds of counter measure devices.

Abstract: A simulator for simulating the firing of a weapon at one or more targets, each target having a respective shape. The simulator includes a housing substantially identical in size and shape to at least a discrete portion of the weapon. The simulator further includes a sensor, operationally connected to the housing, for acquiring a number of images of at least one of the targets. The simulator also includes an image processor for detecting and analyzing change among the images and for initiating control signals based on the analysis.

Abstract: An angular motion measurement system disposed on a movable platform having a first and second section, the system comprising a first and second measurement arrangement and a processor arrangement. The first measurement arrangement provides a first output indicative of angular motion of the first section and has a bandwidth above 50 Hertz and at least one of, a bias above 5 degrees per second and a scale factor above 10%. The second measurement arrangement provides a second output indicative of angular motion of the second section and has a bandwidth below 50 Hertz, a bias below 5 degrees per second and a scale factor below 10%. The processor arrangement is responsive to a plurality of inputs, which include the first and second output, generating a corrected output having a bandwidth above 50 Hertz, a bias below 5 degrees per second and a scale factor below 10%.

Abstract: A method for operating a short range, air-to-air missile carried by an aircraft flown by a pilot. The missile includes a seeker operative to track a target. The method comprises providing a first indication to the pilot when the seeker is tracking a target, providing a second indication to the pilot when a rate of angular motion of the seeker falls below a given value for a predefined period.

Abstract: An optical window assembly including an outer window, an inner window and a housing. The outer window and the inner window are mounted in the housing, holding the outer window and the inner window apart, forming an intervening space between the outer window and the inner window.

Abstract: A warhead configuration for forming a large-diameter hole through a wall of a target includes a shaped charge of explosive material presenting an annular front surface portion circumscribing an axis of the charge. The annular front surface portion exhibits a concave profile as viewed in cross-section through the axis, at least part of the concave profile being configured such that a vector projecting outward from the part normal to the annular front surface portion diverges from the axis. A liner is provided adjacent to at least part of the annular front surface portion.

Abstract: A projectile (100) for piercing armor including a cruise propellant (116) for maintaining a cruise velocity of the projectile. The projectile (100) also includes an acceleration rocket motor (109) activated after launch for accelerating the projectile (100) from the cruise velocity to a penetration velocity, in a final stage of flight of the projectile.

Abstract: A system for the detection and determination of the success of interception of incoming missiles, used in conjunction with a defense weapon system capable of identifying and tracking incoming missiles and interceptors. The system comprises at least one of a plurality of sensing units. Each sensing unit comprises: an optical sensor for detecting optical signals within a predetermined range; tracking means coupled to the optical sensor for tracking an intercepting missile or an incoming missile; processing means for processing optical input detected by the optical sensor and analyzing the optical input to identify an optical signature and determine detonation of interceptor or incoming missile; communicating means for communicating data between the sensing unit and the defense weapon system; and control means for controlling the tracking means, the processing means and the communicating data.

Abstract: A device and method for determining the bearing of an incoming RF signal. The signal is received using a plurality of primary antenna element (5). Each antenna element feeds into a respective receiving channel (6) that downconverts the received RF signal to IF, preferably by mixing with a local oscillator signal. The local oscillator signal may be produced by diverting and combining portions of the received RF signals, by receiving the incoming RF signal using one or more auxiliary antennas (11), or by a tunable oscillator. Preferably, the local oscillator signal is conditioned and filtered before mixing. The IF signals are processed, either by analog or digital means, to infer the bearing of the incoming RF signal.

Abstract: A personal protective shield, which comprises a central panel; at least two lateral panels; and hinged connections between the central panel and the lateral panels. The protective shield has a folded configuration for carrying it and for attaching to it other equipment, in which the aforementioned lateral panels are folded against the central panel, and an expanded configuration for carrying out its protective function, in which the aforementioned lateral panels are angularly set off from the central panel. The central panel and the lateral panels are made of bulletproof plate materials. The central panel may have a curved configuration adapted to fit the back of the user, and the lateral panels may have curved configurations matching that of the central panel.

Abstract: A cylindrical, ray-imaging, electronically steered array antenna, whose radiating array elements are disposed on a cylindrical surface sector above an electrically conductive ground plane that enhances the antenna gain. The conductive ground plane forms an integral part of the antenna, and the required dimensions of this ground plane depend on the array radius, and on the lowest elevation coverage angle from the (possibly tilted) ground plane. The antenna of the present invention is further characterized by a modular design that tailors the required antenna gain and azimuthal directivity through the stacking of identical antenna segments side by side. The antenna design uses the multiple-beam ray focusing property of a microwave lens when feeding a circular ring array, while producing at the same time coherent ray imaging from a bottom metal plate.

Abstract: An airborne platform comprising: (a) an aerodynamic body; (b) a protected element within the aerodynamic body; and (c) a cover, reversibly secured to the aerodynamic body, for protecting the protected element from an external atmosphere. The present invention is particularly suited for an electro-optical detection system equipped with an optical dome or window. Optical windows carried on airborne platforms are known to be particularly sensitive to the high temperatures generated by air friction at super-sonic speeds. By covering such a window when the airborne platform is in flight, and releasing the cover just before use, the electro-optical detection system equipped with the optical window can be made operative, even at airborne platform speeds of several Mach and higher.

Abstract: A planar, ray-imaging, electronically steered array antenna, whose radiating array elements are disposed on a planar surface above an electrically conductive ground plane that enhances the antenna gain. The conductive ground plane forms an integral part of the antenna, and the required dimensions of this ground plane depend on the array height, and on the lowest elevation coverage angle from the (possibly tilted) ground plane. The antenna is further characterized by a modular design that tailors the required antenna gain and azimuthal directivity through the stacking of identical antenna segments side by side. The antenna can generate, with the aid of a multiple-beam microwave network or a two-ended series-feed network, a pair of symmetrically steered beams from an incident wavefront received by a linear (column) or planar array, in conjunction with reflections from a bottom metal plate.

Abstract: Method of shaping solid, particulate materials, which comprises forming a raw slurry of the starting material, in a liquid which is a partial solvent of said material, and submitting the slurry to treatment by ultrasound generators to produce therein ultrasonic vibrations which shape and grind the starting, particulate material to produce a shaped slurry of ground and shaped particles. The shaped particles may be separated from their slurry by removing the partial solvent by decantation and/or filtration. The partial solvent may be a liquid in which the material to be shaped has a solubility comprised between 1 and 10, wherein the solubility is expressed as grams of material that are dissolved in 100 ml of the liquid at a temperature of 20° C. The partial solvent can be chosen from among acetone, methyl ethyl ketone, and mixtures of said solvents with one another or other solvents and/or a minor amount of water, and may also be an organic solvent.

Abstract: A warhead configuration for forming a large-diameter hole through a wall of a target includes a shaped charge of explosive material presenting an annular front surface portion circumscribing an axis of the charge. The annular front surface portion exhibits a concave profile as viewed in cross-section through the axis, at least part of the concave profile being configured such that a vector projecting outward from the part normal to the annular front surface portion diverges from the axis. A liner is provided adjacent to at least part of the annular front surface portion.

Abstract: A warhead (10) configuration for forming a large-diameter hole through a wall of a target includes a shaped charge of explosive material (12) presenting an annular front surface portion (16) circumscribing an axis of the charge. The annular front surface portion (16) exhibits a concave profile as viewed in cross-section through the axis, at least part of the concave profile being configured such that a vector projecting outward from the part normal to the annular front surface portion diverges from the axis. A liner (14) is provided adjacent to at least part of the annular front surface portion.

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 defeating a threat posed by a guided missile. The system includes a broad band light source with a beam width of less than 4°, a DIRCM control system, a missile warning system, and a missile tracking system. The DIRCM control system is configured to aim a beam produced by the light source. The missile warning system is configured to supply the DIRCM control system with a first trajectory of the missile. The missile tracking system is configured to supply the DIRCM control system with a second trajectory of the missile, which is more accurate than the first trajectory.

Abstract: A remotely-controlled unmanned mobile device (UMD) adapted to function as a robot scout to enter and reconnoiter the site of a disaster and to communicate to a rescue mission information regarding conditions prevailing at the site, making it possible for the mission to decide on rescue measures appropriate to these conditions. The UMD is operable in either of two modes. In its air-mobility mode the UMD is able to vertically take off and land, to fly to the site and then hover thereover. In its ground-mobility mode, the UMD can walk on legs over difficult terrain and through wrecked structures and ruins. The UMD is provided with condition-sensitive sensors for gathering data regarding conditions prevailing at the site, and position-sensitive sensors for avoiding obstacles in the path of the walking UMD, thereby assuring safe mobility. Other sensors govern geo-referenced navigation and flight control functions.

Abstract: A method for boresighting of a designation system, including a tracker responsive to a detector with reference to an indicator, including the step of directing a beam of light at a target, using a light source, so that the beam of light is reflected from a spot on the target while a temperature of the spot remains substantially constant. The method further includes focusing at least part of the reflected light as an image on the detector and determining a misalignment of the indicator and the image.