ISRAEL AEROSPACE INDUSTRIES LTD.

Distributed radar systems and techniques for processing data received from such distributed radar systems. The distributed radar systems may utilize data on beam spatial pattern for processing collected signals and determining direction of one or more reflection origins (e.g., one or more objects reflecting transmitted signal).

A marine vessel management system, comprising: receiving input data comprising at least radar input data indicative of a first field of view and imagery input data indicative of a second field of view being at least partially overlapping with said first field of view. Processing the input data to determine data indicative of reflecting object(s) within an overlapping portion of said first field of view. Determining respective locations(s) within said second field of view, where said reflecting object(s) are identified, and obtaining radar meta-data of said reflecting object(s); processing said input imagery data said respective locations in an overlapping portion of said second field of view. Determining image data piece(s) corresponding with section(s) of said imagery data associated with said reflecting object(s). Using said radar meta-data for generating label data and generating output data comprising said image data section(s) and said label data.

Using a e.g. said hardware processor, comparing said estimate of current GNSS quality, for each vehicle in a fleet of interest to the client, to a GNSS quality target value, and, on at least one occasion in which a vehicle in the fleet of interest to the client is found to differ unacceptably from the GNSS quality target value, commanding an actuator to take at least one corrective measure, thereby to yield GNSS quality monitoring functionality.

A boom member for in-flight refueling includes a first boom member portion, a second boom member portion, and a connect/disconnect mechanism. The first boom member portion includes a first boom lumen, a first boom axis, and a fuel receiving end. The second boom member portion includes a second boom lumen, a second boom axis, and a fuel delivery end including a fuel delivery nozzle. The connect/disconnect mechanism is configured for: selectively enabling the first boom member portion to be connected with respect to the second boom member portion to provide a connected configuration; and, for selectively enabling actively disconnecting the first boom member portion with respect to the second boom member portion to provide a disconnected configuration responsive to receiving a disconnection activation signal.

A phased array antenna comprising a plurality of antenna modules, each antenna module comprising a radiating element made of an electrically conductive material printed on a fabric substrate by a screen-printing process and/or an inkjet printing process; and, a signal input port comprising at least one probe electrically coupled to said radiating element, said probe being configured to be coupled to a corresponding transceiver module so that an amplitude and phase of each of said radiating elements can be independently controlled. Further, a method for manufacturing the phased array antenna, comprising: printing an electrically conductive material on a fabric substrate by a screen-printing process and/or an inkjet printing process, so as to form said radiating element for each of the antenna modules; and for each of the antenna modules, electrically coupling said radiating element to said signal input port, thereby assembling the plurality of antenna modules.

An energy attenuation system for a seating system (having a bucket and a frame includes at least one energy attenuation component operatively coupled with a fuse system. The energy attenuation component includes first and second ends securable to the bucket and the frame, respectively. The fuse system includes a plurality of fuse elements and an engagement element. Each fuse element has a first and second fuse ends, and operates to break under a corresponding predetermined fixed load. The engagement element is movable with respect to the fuse elements and is engageable in a load bearing manner via the respective said second fuse ends thereof with any desired fuse element group chosen, each fuse element group including one or more fuse elements. The engagement element is securable to the bucket or the frame, and the first fuse ends of all the fuse elements are securable to the frame or bucket, respectively.

A flight simulation system for enabling g-force training includes a seating system, a sensor arrangement, and a controller. The seating system is configured for accommodating a human occupant and for providing thereto physically simulated flight conditions corresponding to predetermined real flight conditions, the predetermined real flight conditions including g-forces, wherein the physically simulated flight conditions include application of non-g forces to the human occupant corresponding to the g-forces, and wherein the g-forces are considered sufficient to provide g-force induced physiological stress to the human occupant. The sensor arrangement is configured for providing real-time feedback data of predetermined physiological parameters of the human occupant, in operation of the flight simulation system with the human occupant accommodated in the seating system, wherein the predetermined physiological parameters are indicative of the g-force induced physiological stress. The controller is configured for controlling the seating system to provide the physically simulated flight conditions.

A new axisymmetric Coriolis vibrating gyroscope includes a resonator configured to vibrate in a standing wave; a plurality of control elements; and a control circuitry, configured to iteratively control said control elements so as to maintain an angular direction of said vibration at a current setpoint; determine an angular direction of said vibration of said resonator from respective readings of at least two of said control elements; calculate a total angular rate; and update said setpoint to an angular direction of said vibration determined in a previous iteration

A system for finding a target direction, the system comprising a gyroscope and/or an accelerometer perpendicular to the gyroscope and/or a rotating stage on which the gyroscope and accelerometer are mounted, and/or a hardware processor configured for computing a first azimuthal orientation which points to a horizontal direction, based on readings taken when the gyroscope and accelerometer are in a first azimuthal position; and/or an estimation of a required direction based on: at least one gyroscope reading and at least one accelerometer reading in the first azimuthal position and/or at least one gyroscope reading and at least one accelerometer reading in a second, opposite azimuthal position 180 degrees away from the first position.

An air intake module for a projectile includes a module forward end (MFE), a module aft end (MAE), and an aft facing intake cone arrangement (AFICA). The air intake module is configured for connection to the forward portion and the propulsion system of the projectile. The MAE is longitudinally displaceable with respect to the MFE between a stowed configuration (wherein the MFE is at a first spacing with respect to the MAE) and a deployed configuration (wherein the MFE is at a second spacing, greater than the first spacing). The AFICA includes a plurality of intake cone elements, each being pivotably movable between an open position (corresponding to the stowed configuration) wherein the intake cone elements are overlying the MAE, and a closed position (corresponding to the deployed configuration) wherein the intake cone elements are pivoted towards one another to form an aft facing cone structure forward of the MAE.