Abstract: A method for processing and analyzing digital terrain data utilizing Digital Terrain Elevation Data (DTED). The method comprises defining approach azimuth and visibility limitations angle which are used for defining directional fans by determining fan opening angle, fan azimuth, and maximal range for terrain analysis. At least one directional fan data set is constructed from at least one source point within the DTED, where the directional fan includes line of sight information between said source point and DTED points located within said directional fan. The method further comprises interrogating said data sets by one or more queries to obtain terrain information for given approach conditions.

Abstract: A helmet position measuring system for use in a predefined environment. The system includes a helmet-mounted illumination system for directing electromagnetic radiation of one or more wavelength from the helmet in one or more range of angles, a set of three or more passive reflectors deployed at fixed positions in the predefined environment to reflect electromagnetic radiation from the illumination system, a helmet-mounted imaging system sensitive to the one or more wavelength for deriving images of part of the predefined environment including electromagnetic radiation reflected from the reflectors, and a processing system associated with the imaging system for processing the images to identify regions of the images corresponding to the reflectors and hence to determine information relating to a position of the helmet within the predefined environment.

Abstract: A radar decoy having radar reflectors disposed in the interior of the inflated canopy of a descending parachute as a first set of four corner reflectors, and a second set of corner reflectors disposed on the exterior of the canopy integral with the first set of corner reflectors, to form an octahedron of eight corner reflectors. The radar decoy is pliable and folded with the parachute for stowage in the interior of a canister. When loaded on a vehicle flying in a trajectory, the canister may open at a point P on the trajectory, to release the parachute, and thereby deploy the radar decoy to become operative.

Abstract: The present invention relates to process for producing a transparent missile dome having a spanning angle larger than 180°, comprising the step of: (a) growing from single crystals of a ceramic material a first dome portion, said first dome portion being a portion of a sphere (b) growing from single crystals of a ceramic material a second dome portion, said second dome portion being a complementary sphere-portion for said first dome portion (c) attaching said complementary dome portion to said first dome portion and to the body of the missile, thereby forming a missile with a front dome having a spanning angle larger than 180°.

Abstract: A highly-filled paste, and a method and device of de-aerating and injecting the paste, the paste including: (a) a solid filler; (b) an organic binder, and (c) a residual gas, wherein the paste contains at least 80 volume-% of the solid filler and has a viscosity exceeding 100 kilopascal·seconds, wherein the filler, binder, and residual gas are intimately mixed so as to form a substantially homogeneous paste, and wherein a composition of the solid filler, binder, and residual gas is selected such that the homogeneous paste has: an average density greater than 98.5% of a Theoretical Maximum Density (TMD).

Abstract: A airborne reconnaissance system comprising: (1) Gimbals having at least two degrees of freedom; (2) At least one array of light sensors positioned on the gimbals, for being directed by the same within at least two degrees of freedom; (3) Map storage means for storing at least one Digital Elevation Map of an area of interest, divided into portions; (4) Inertial Navigation System for real-time providing to a gimbals control unit navigation and orientation data of the aircraft with respect to a predefined global axes system; (5) Portion selection unit for selecting, one at a time, another area portion from the area of interest; and (6) servo means for directing the gimbals. The system uses data from the inertial navigational system and from the digital elevation map for real-time calculating direction to selected area portions, and for maintaining the direction during integration of light from the terrain, and for producing corresponding images of area portions.

Abstract: A simulant material for simulating hazardous materials, comprising a quantity of at least one explosive material and at least one inert material. The simulant material is a non-explosive material and is in the form of a homogenous, flexible and non-particulated material.

Abstract: A Controlled-Harm Explosive Reactive Armor (COHERA) is made of explosive layered between two plates of material with predetermined fragmentation having controlled harm prevention properties. The fragmentation is predetermined and prevents harm to personnel and equipment nearby a reacting COHERA. The controlled harm prevention qualities of a COHERA are determined according to a Harm Specification and to accompanying harm delimiting parameters. Furthermore, the COHERA is configured to prevent sympathetic initiation.

Abstract: A method for deriving three-dimensional information progressively from a streaming video sequence.

Abstract: The present invention is a propulsion kit that is attached to a gliding air to surface bomb. The kit of the invention comprises one or more engines and, when activated, allows a significant extension of the length of the flight path of the bomb. The engines can be any type of air-breathing engine for example jet engines. The kit can be designed to be retrofitted to an existing gliding bomb. The kit of the invention allows the original bomb to function in one of the three following modes, depending on the bomb size and the aerodynamic characteristics: the original operation mode, an improved gliding ratio mode, and a cruise trajectory mode.

Abstract: The invention relates to the use of ceramic, plasma-deposited, layers for manufacturing plastic articles whose function requires low-friction surface. The invention further provides a process of manufacturing a polymer object having a low-friction surface, comprising i) providing a mold defining the shape of said object; ii) coating said mold that defines the shape of said low-friction surface with a ceramic layer, the layer being formed by plasma deposition; and iii) molding the polymer in said mold. The invention also provides a polymer article having a low-friction surface created by molding on a plasma-deposited ceramic surface.

Abstract: A device for fiber optic free-space optical communication between electronic components, having no physical communication connection, in which terminal ends of optical fibers are aligned such that light emitting from the terminal end of one optical fiber is transmitted across free-space and received by the terminal end of another optical fiber. The light thusly received is transmitted to a corresponding transceiver, to which the optical fiber is connected, deployed on the electronic component, thereby establishing optical communication between two transceivers across the free-space separating the two terminal ends.

Abstract: The present invention relates to an airborne reconnaissance system for capturing images in a wide field of regard which comprises: (a) An array of a plurality of n prisms being one next to the other, each prism having an essentially flat and rectangular front surface, and at least an output surface wherein: (a1) a front surface of each of the plurality of prism is being directed toward a different section of a strip of terrain transversal to the flight direction of the aircraft, thereby collecting light rays coming mostly from that terrain strip section; (a2) each output surface of each of the prisms directs light rays which are received through said front prism surface toward a front lens of an optical unit; (b) A focal plane array; (c) Optical unit comprising a front lens, the front lens receiving light separately but simultaneously through the output surfaces of all the prisms, said optical unit comprises addition optics for directing the light received from said lens thereby to produce separate correspond

Abstract: A submarine floating periscope comprising: (a) a floating base; (b) a scanning unit for scanning and acquiring images, and; (c) cables between the submarine and the periscope for maintaining the periscope in the vicinity of the submarine, and for enabling communication between the periscope and the submarine. The scanning unit comprises: (i) a transparent dome; (b) a two-degrees of freedom gimbals system in a hollow portion below the dome. The gimbals system includes a mechanism for changing the orientation of a plate within the hollow portion by applying rotation about two perpendicular axes; (c) a light sensing element, for sensing light coming from outside the dome thereby forming images, the sensing unit being positioned on said plate, preferably in its center; and (d) a modem for transferring images data and other data between the periscope and the submarine.

Abstract: A modular launch-cell system for a launch vehicle. The method includes a number of launch-cells, a base and an upper attachment arrangement. The launch-cells include a missile and are arranged in a structure which includes a number of layers, each of the layer includes two or more launch cells. The launch-cells are substantially directly reversibly mechanically connected to the base. One of the launch-cells includes a lower attachment arrangement configured for reversibly mechanically connecting one launch-cell to one or more of the base and another of the launch-cells disposed below the one launch-cell. The upper arrangement is designed for reversibly mechanically connecting one launch-cell to another of the launch-cells disposed above the one launch-cell.

Abstract: An apparatus and method for winding an optical fiber of arbitrary diameter on a smooth conical bobbin. The apparatus includes a slotted helical ring (148) attachable to, or integrated with a bobbin, the ring used to guide a fiber (152) in its initial first turn in the winding. After the first turn, the winding of a base layer and subsequent layers is achieved without needing a grooved bobbin surface.

Abstract: A LADAR system includes a detector optical arrangement defining a current optical field of view. An illumination subsystem without moving parts transmits pulsed illumination at different times to each of a number of illumination sub-regions of the current optical field of view, and a detection subsystem, including one or more detectors, detects reflected illumination from a corresponding one or more detection sub-region of the current optical field of view. Each of the detection sub-regions overlaps illumination sub-regions so that an overlap of each of the illumination sub-regions with the detection sub-region defines a LADAR image pixel of resolution finer than the detection sub-region.

Abstract: A system for identifying flash events including an optical imaging module with one or more optical imaging array, the optical imaging module configured for monitoring a region of interest to identify a tentative flash event. The system further includes a ranging module associated with the optical imaging module and configured to derive an estimated range to a location of the tentative flash event, and an acoustic verification module associated with the ranging module and with one or more acoustic sensor. The acoustic verification module is configured to determine whether an acoustic event corresponding to the tentative flash event is detected within a time window derived from the estimated range, thereby classifying the tentative flash event as either a verified flash event or a rejected flash event.

Abstract: A airborne reconnaissance system comprising: (1) Gimbals having at least two degrees of freedom; (2) At least one array of light sensors positioned on the gimbals, for being directed by the same within at least two degrees of freedom; (3) Map storage means for storing at least one Digital Elevation Map of an area of interest, divided into portions; (4) Inertial Navigation System for real-time providing to a gimbals control unit navigation and orientation data of the aircraft with respect to a predefined global axes system; (5) Portion selection unit for selecting, one at a time, another area portion from the area of interest; and (6) servo means for directing the gimbals. The system uses data from the inertial navigational system and from the digital elevation map for real-time calculating direction to selected area portions, and for maintaining the direction during integration of light from the terrain, and for producing corresponding images of area portions.