Provided is an apparatus for detecting airborne objects comprising a kill vehicle bus having a radar sensor. The radar sensor may be an interferometric sensor comprising a plurality of transmit-receive arrays. Each of the transmit-receive arrays may be adapted to be stowed in a stowed position in or on the kill vehicle bus, and may be adapted to be expandable from the stowed position to an operable position.

An optical radiation-collecting assembly includes a convex mirror, a concave mirror with a central opening and a window, arranged such that light passes through the opening in the concave mirror, is reflected first by the convex mirror and then by the concave mirror, and subsequently passes through the window. The optical assembly is suitable for use in a homing device for guiding a rocket, preventing an optical input component of such a device from being damaged and rendered inoperative from abrasion when exposed to a high-speed air flow containing dense particles. The optical assembly also includes an image-forming function.

According to various aspects and embodiments, a system and method for providing an optical element is disclosed. In one example, the optical element includes a substrate formed from a Nanocomposite Optical Ceramic (NCOC) material that includes a first oxide nanograin material dispersed in a second oxide nanograin material, and a compressive layer of the NCOC material formed on a surface of the substrate.

A spatially-distributed architecture (SDA) of antennas transmits respective uniquely coded signals. A first receiver having a known position in a coordinate system defined by the SDA receives reflected versions of the uniquely coded signals. A first processor receives the reflected versions of the uniquely coded signals and identifies a position of a non-cooperative object in the coordinate system. A platform with a platform receiver receives non-reflected versions of the uniquely coded signals. The platform determines a position of the platform in the coordinate system. In an example, the platform uses a self-determined position and a position of the non-cooperative object communicated from the SDA to navigate or guide the platform relative to the non-cooperative object. In another example, the platform uses a self-determined position and information from an alternative signal source in a second coordinate system to guide the platform. Guidance solutions may be generated in either coordinate system.

A battlefield weapon system is proposed to counter the threat posed by small drones. The main system element is an aerodynamically guided missile that is compatible with existing multipurpose shoulder launched weapon systems. The system is fully portable for dispersed deployment among infantry.

A compact, wideband antenna system includes first and second monopole radiating elements positioned near an edge of a common ground plane. The first and second monopole radiating elements may be located on opposite sides of the ground plane. Additional monopole elements may also be provided. In some embodiments, the ground plane includes an opening in a central region thereof to accommodate an optical system. In some embodiments, an additional antenna (e.g., an array antenna) may be provided over the same ground plane in a region between the monopole elements.

A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.

A method for automatically generating a three-dimensional reference model as terrain information for a seeker head of an unmanned missile. A three-dimensional terrain model formed from model elements obtained with the aid of satellite and/or aerial reconnaissance is provided. Position data of the imaging device at least at one planned position and a direction vector from the planned position of the imaging device to a predetermined target point in the three-dimensional terrain model are provided. A three-dimensional reference model of the three dimensional terrain model is generated that incorporates only those model elements and sections of model elements from the terrain model, which in the viewing direction of the direction vector from the planned position of the imaging device, are not covered by other model elements and/or are not located outside the field of view of the imaging device.

A method steers a missile towards a flying target. In order to permit precise flight to the target even under poor visibility conditions owing to the weather, a radar which is remote from the missile detects the target and transmits data relating to a first location area of the target to the missile. The missile determines, from the data of its own missile radar, a second location area of the target, processes both location areas to form a target area and flies to the target area.

A guided munition system includes a munition body including at least one fluid dynamic control for changing course of the munition body in flight. A seeker onboard the munition body is operatively connected to control the at least one fluid dynamic control. The seeker includes a coded aperture imaging device facing outward from the munition body for image based control for guiding the munition body in flight.