Abstract: The presently disclosed subject matter includes a system and a method for launching a projectile towards a target, wherein the system comprises a control circuitry, a booster engine, and one or more thrusters adapted to be connected to the projectile and capable of being spun during launch around a longitudinal axis of the projectile, the control circuitry being operatively connected to the one or more thrusters; wherein responsive to ignition of propellant stowed in a combustion chamber of the booster engine, the booster engine causes the projectile to launch from its cell; following launch of the projectile, cause the projectile to turn at a certain rate and a certain azimuth.

Abstract: The presently disclosed subject matter includes a system and a method for launching a projectile towards a target, wherein the system comprises a control circuitry, a booster engine, and one or more thrusters adapted to be connected to the projectile and capable of being spun during launch around a longitudinal axis of the projectile, the control circuitry being operatively connected to the one or more thrusters; wherein responsive to ignition of propellant stowed in a combustion chamber of the booster engine, the booster engine causes the projectile to launch from its cell; following launch of the projectile, the control circuitry is configured to activate one or more thrusters that cause the projectile to turn at a certain rate and a certain azimuth.

Abstract: The presently disclosed subject matter includes a computerized method and system for determining miss-distance between platforms. The proposed method and system make use of an electro optic sensor (e.g. camera) mounted on one of the platforms for obtaining additional data which is used for improving the accuracy of positioning data obtained from conventional positioning devices. A navigation error is calculated where the relative position of the two platforms is converted to the camera reference frame. Once the navigation error is available, it can be used to correct a measured miss-distance.

Abstract: A fragmentation warhead is provided, capable of being mounted in a carrier vehicle, the warhead having a longitudinal axis. In at least one example the warhead includes a shell that extends along the longitudinal axis. The shell includes a fixed shell portion and a fragmentation portion, and defines therebetween a cavity for accommodating therein an explosive charge. The fragmentation portion includes at least one set of serially adjacent fragments in correspondingly serially contiguous relationship in the fragmentation portion and in generally helical relationship with respect to the longitudinal axis. A corresponding carrier vehicle and a corresponding missile are also provided.

Abstract: The presently disclosed subject matter includes a computerized method and system for determining miss-distance between platforms. The proposed method and system make use of an electro optic sensor (e.g. camera) mounted on one of the platforms for obtaining additional data which is used for improving the accuracy of positioning data obtained from conventional positioning devices. A navigation error is calculated where the relative position of the two platforms is converted to the camera reference frame. Once the navigation error is available, it can be used to correct a measured miss-distance.

Abstract: A fragmentation warhead is provided, capable of being mounted in a carrier vehicle, the warhead having a longitudinal axis. In at least one example the warhead includes a shell that extends along the longitudinal axis. The shell includes a fixed shell portion and a fragmentation portion, and defines therebetween a cavity for accommodating therein an explosive charge. The fragmentation portion includes at least one set of serially adjacent fragments in correspondingly serially contiguous relationship in the fragmentation portion and in generally helical relationship with respect to the longitudinal axis. A corresponding carrier vehicle and a corresponding missile are also provided.

Abstract: A fragmentation warhead is provided, capable of being mounted in a carrier vehicle, the warhead having a longitudinal axis. In at least one example the warhead includes a shell that extends along the longitudinal axis. The shell includes a fixed shell portion and a fragmentation portion, and defines therebetween a cavity for accommodating therein an explosive charge. The fragmentation portion includes at least one set of serially adjacent fragments in correspondingly serially contiguous relationship in the fragmentation portion and in generally helical relationship with respect to the longitudinal axis. A corresponding carrier vehicle and a corresponding missile are also provided.

Abstract: There is provided an inflatable dummy target comprising a chassis wrapped with a sheet. The chassis can be formed by individual inflatable ducts and can comprise at least two ring-shaped ducts interconnected by one or more elongate ducts. The inflatable dummy target can further comprise rigidizing ducts. The inflatable dummy target geometry can be conical, cylindrical, etc. Optionally, the inflatable dummy target can comprise several attached axi-symmetrical sections, wherein each section has a chassis wrapped with a sheet, the chassis formed by individual inflatable ducts. Optionally, the shape of each section can be selected from the group consisting of conical, frustoconical and cylindrical forms.

Abstract: A computer-implemented method for detecting an unattended living presence in a vehicle having at least two doors, comprising determining, before the vehicle starts moving, a first total number of vehicle door openings utilizing a non added-on door sensor integrated in the vehicle, each of the door sensors is associated with at least one of the at least two doors and is indicative of a door state, wherein each opening of a door indicates a change in a door state of a door, out of the at least two doors, from a door closed state to a door open state; determining, after the vehicle has stopped moving and until being locked, a second total number of vehicle door openings utilizing the non added-on door sensors; and in case the first total number exceeds the second total number, outputting an alert on a possible unattended living presence in a vehicle.

Abstract: An inflatable dummy target fittable into a carrier missile capable of being released from the carrier missile during exo-atmospheric flight; upon release, the dummy target or portion thereof is capable of being inflated and manifest characteristics that resemble GTG missile characteristics, wherein the GTG missile characteristics include IR signature, RF signature and GTG missile.

Abstract: A counter-flying object system comprising a sensor array including at least one active sensor configured to detect and track the flying object, and a missile launcher configured to launch an interceptor to intercept the flying object, wherein upon launching of the interceptor, the sensor array is configured to determine the location of the interceptor and send said object and interceptor locations to a control system, the control system being configured to provide mission data to the interceptor based on said object and interceptor locations for guiding the interceptor toward the flying object and activating a fragmentation warhead on or in the vicinity of said flying object when a lethality criteria is met.

Abstract: A fragmentation warhead is provided, capable of being mounted in a carrier vehicle, the warhead having a longitudinal axis. In at least one example the warhead includes a shell that extends along the longitudinal axis. The shell includes a fixed shell portion and a fragmentation portion, and defines therebetween a cavity for accommodating therein an explosive charge. The fragmentation portion includes at least one set of serially adjacent fragments in correspondingly serially contiguous relationship in the fragmentation portion and in generally helical relationship with respect to the longitudinal axis. A corresponding carrier vehicle and a corresponding missile are also provided.

Abstract: A counter-flying object system that includes a sensor array including an active sensor for detecting and tracking the flying object. An interceptor missile launcher for launching an interceptor to intercept the flying object, wherein upon launching of the interceptor, the sensor array determines the location of the interceptor and sends the object's and interceptor's locations to a control system. The control system provides mission data to the interceptor based on the object's and interceptor's locations for guiding the interceptor toward the flying object and activating a fragmentation warhead on or in the vicinity of the flying object when a lethality criteria is met.

Abstract: An inflatable dummy target fittable into a carrier missile capable of being released from the carrier missile during exo-atmospheric flight; upon release, the dummy target or portion thereof is capable of being inflated and manifest characteristics that resemble GTG missile characteristics, wherein the GTG missile characteristics include IR signature, RF signature and GTG missile.

Abstract: A counter-flying object system comprising a sensor array including at least one active sensor configured to detect and track the flying object, and a missile launcher configured to launch an interceptor to intercept the flying object, wherein upon launching of the interceptor, the sensor array is configured to determine the location of the interceptor and send said object and interceptor locations to a control system, the control system being configured to provide mission data to the interceptor based on said object and interceptor locations for guiding the interceptor toward the flying object and activating a fragmentation warhead on or in the vicinity of said flying object when a lethality criteria is met.

Abstract: A system for instantaneous and continuous nanosecond-level accuracy determination of a relative time offset between at least two non-collocated timing units, the system including at least two non-collocated timing units located at known positions, each timing unit comprising a frequency source and a collocated receiver, each frequency source being disciplined at a frequency domain using a time source to generate corrections of the relative frequency drift between the frequency source and the time source.

Abstract: An exo-atmospheric intercepting method for intercepting in space multiple objects, including acquiring and tracking multiple inflated objects which fly towards a protected territory. The method further includes launching an interceptor missile accommodating a plurality of kill vehicles each hosting a plurality of punching objects and classifying the multiple objects into clusters. In respect of each cluster of objects, determining an ejection condition responsive to meeting of which a kill vehicle is ejected from the interceptor missile towards the cluster of objects and thereafter releasing from the kill vehicle a plurality of punching objects such that every inflated object in the cluster is likely, with a high degree of certainty, to be punched by one or more punching objects.

Abstract: An inflatable dummy target fittable into a carrier missile capable of being released from the carrier missile during exo-atmospheric flight; upon release, the dummy target or portion thereof is capable of being inflated and manifest characteristics that resemble GTG missile characteristics, wherein the GTG missile characteristics include IR signature, RF signature and GTG missile.

Abstract: A system for instantaneous and continuous nanosecond-level accuracy determination of a relative time offset between at least two non-collocated timing units, the system comprising at least two non-collocated timing units located at known positions, each timing unit comprising a frequency source and a collocated receiver, each frequency source being disciplined at a frequency domain using a time source to generate corrections of the relative frequency drift between the frequency source and the time source.

Abstract: Method for providing a known reference point for an airborne imaging system, the method including providing at measured earth co-ordinates a camera/mirror assembly having a camera and a mirror mounted in fixed mutual spatial relationship and capable of tilting about two mutually orthogonal axes. Using the camera to track the sun and produce at least two or more different measured times respective time tagged camera images. Using the time tagged camera images to obtain a transformation of mirror axes relative to axes of the earth at a mirror location on the earth where the mirror is mounted. During a time window when the mirror is within a line of sight of the airborne imaging system and the sun, adjusting the azimuth and elevation of the mirror so that the sun is reflected by the mirror toward the airborne imaging system thereby capturing an image of the mirror in an aerial image produced by the airborne imaging system.