Abstract: A method for directing a laser pulsed beam towards a selected area/surface of an object, comprising transmitting from a laser assembly that includes an optical transmitter module a pulsed laser beam having a first pulse duration and illuminating therewith an area/surface of the object, thereby obtaining a reflected pulsed laser beam, the reflected pulsed laser beam including a leading portion reflected from a first reflecting area/surface of the object which is the area of the object that defines the shortest optical path between the optical transmitter module, the object and an optical receiver module; receiving, in a second laser assembly that includes the optical receiver module, the reflected pulsed laser beam and converting it into an amplified phase conjugated pulsed beam of a second pulse duration, and transmitting from the second laser assembly the amplified phase conjugated pulsed beam and illuminating therewith on selected area/surface of the object.

Abstract: A method of determining a direction of a target in a ground referential, the method including: acquiring an image of a scene including the target and a control object using a camera; obtaining position data of the camera and control object using a geo-spatial positioning system; determining a control direction from the camera to the control object in the ground referential using the position data; estimating a camera attitude in the ground referential using the control direction; determining the target direction from the camera to the target using the estimated camera attitude and a pixel position of the target in the image.

Abstract: An airplane transfer system for transferring an airplane comprising an airplane control component. The system comprises: a transfer module comprising at least one motor and adapted to transfer an airplane; and a controller coupled to the transfer module and configured to: i) receive a at least one transfer signal that is responsive to one or more commands provided via the airplane control component; and ii) control the transfer module in response to the transfer signal, wherein the commands are a priori capable of controlling the airplane or components thereof.

Abstract: The disclosure presents at least one example of a missile system, method, and/or computer program product. The missile system may, for example, include a radar, an Automatic Dependent Surveillance Broadcast (“ADS-B”) receiver, a missile launcher, and a control station. The missile system may, for example, be configured to handle various situations such as when only ADS-B data relating to an airborne entity is available, only radar data relating to the airborne entity is available or both ADS-B data and radar data relating to the airborne entity are available. The missile system, may, for example, be a surface to air missile system.

Abstract: A method of georeferencing a first image of a scene acquired from a first imaging device based on at least one second image of the scene acquired from a second imaging device. The method includes obtaining data indicative of an eligibility parameter for one or more areas of the scene; selecting one or more pivot areas among the one or more areas of the scene, wherein the eligibility parameter of the pivot areas satisfy a predefined criterion; for at least some of the selected pivot areas, identifying tie points for the first and second images; and solving the external orientation of the first image using the identified tie points and a first imaging device model.

Abstract: A warhead configured for being mounted in a missile for hitting a target, the warhead comprising: a shell having a rotational symmetry about a longitudinal axis; a shell effective sector extending along said axis, with first and second pluralities of weakenings in said shell, each extending along and having respective first and second orientations relative to said longitudinal axis, such that upon exertion of an explosion force on the weakenings from a corresponding first or second direction, respective first or second explosion fragments are generated; and a first surface and a second surface, each extending along the longitudinal axis, and defining, together with said shell effective section, a cavity for accommodating an explosive charge; each of said surfaces being oriented so that upon initiation of detonation of the explosive charge adjacent to said first or said surface, shock waves propagating therefrom are directed towards the respective first or second plurality of weakenings in said respective firs

Abstract: An engine system with advance detection of detonation and/or pre ignition, the system comprising an engine, operative for propulsion of a vehicle by generating rotational motion, whose rotational velocity over time is monitored; and a detonation and/or pre ignition detector operative to provide an alert for impending detonation and/or pre ignition of the engine, if the rotational velocity fluctuates over time to an extent which is predetermined to be unsafe.

Abstract: The subject matter disclosed herein includes, inter alia, a method and system which enables to determine the steering-angle between the longitudinal axis of a tractor and the longitudinal axis of an aircraft which is being led by the tractor (referred to herein as “steering-angle” in short). While an aircraft is being led, the steering-angle can be repeatedly calculated and compared to a threshold value defining a mechanical steering limit. In case the comparison complies with one or more predefined conditions (e.g. the steering-angle is equal or smaller the threshold value) a warning can be generated indicating to an operator that the steering-angle has reached (or is about to reach) its limit and should be adjusted accordingly.

Abstract: A method of testing a frequency synthesizer over a predetermined frequency range using a delay unit complying with a spectral delay distribution model modeling a spectral delay distribution of the delay unit over the predetermined frequency range. The method comprises generating at least one test signal with the frequency synthesizer according to at least one test command; passing the at least one test signal through the delay unit so as to obtain at least one delayed test signal; measuring at least one shift of a signal attribute between the delayed test signal and the test signal; estimating an accuracy of the frequency synthesizer by comparing the at least one measured shift with an expected shift, the expected shift being derived from the spectral delay distribution model of the delay unit and from the at least one test command.

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: Disclosed a method of transferring airplanes and an unmanned airplane transfer system. The transfer system comprises a transfer module adapted to transfer an airplane by moving a landing gear of the airplane; and a controller being assembled with the transfer system, coupled to the transfer module, and adapted to i) receive a transfer signal; ii) to control the transfer module in response to the transfer signal; and iii) to coordinate transferring the airplane by the unmanned airplane transfer system and at least one second unmanned airplane transfer system. The method of transferring an airplane by a plurality of unmanned airplane transfer systems comprises receiving by at least one unmanned airplane transfer system among said plurality of transfer systems a transfer signal, and in response to the transfer signal, coordinating the transfer of the airplane by at least two unmanned airplane transfer systems among said plurality of transfer systems.

Abstract: Provided is a system for reducing damage by missiles to a vehicle, the system including: (a) a detector operable to detect a missile and to generate detection information indicative of a motion of the missile; (b) a processor, configured to analyze the detection information and to selectively trigger activation of a jetting system that is mounted on the vehicle in response to a result of the analysis; and (c) the jetting system, operable to jet a high pressure jet onto the missile.

Abstract: The invention relates to a plane tractor which grips the nose gear of a plane, including: a chassis; wheel modules connected to the chassis, each wheel module including at least one actuator for inducing a vertical movement of the module in relation to the chassis; a gripping platform for gripping the nose gear of a plane, the platform together with the chassis having freedom of movement substantially in circular translation; and a damping and actuating means connecting the platform and the chassis.

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 refueling device for use in in-flight refueling operation between a tanker aircraft and a receiver aircraft includes a selectively steerable body and a controller. The selectively steerable body configured for being towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and includes a boom member having a boom axis and configured to enable fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during the in-flight refueling operation. The controller is configured for selectively steering the body to an engagement enabling position spaced with respect to the receiver aircraft and for aligning the boom axis in an engagement enabling orientation at the spaced position, and for subsequently moving the boom member along the boom axis towards the receiver aircraft for enabling fuel communication therebetween.

Abstract: An optical system (20) is presented, which is configured to enable the line of sight stabilization. The system comprises a light module (230), an optical module (210) defining an optical axis (0X) and an optical path of light propagation therethrough, and a stabilizer (220) configured and operable for providing optical coupling between said optical module (210) and said light module (230). The stabilizer (2209 comprises: a gimbal assembly defining a first rotation axis (FRX) orthogonal to said optical axis (0X), and an internal deflector (222) located in the optical path of light propagating through said optical module (210). The internal deflector (222) is mounted for rotation about said first rotation axis (FRX) and is configured and operable to provide optical coupling between at least a section of the optical path of said optical module (210) and an optical path of light passing through said light module (230).

Abstract: An unmanned airplane transfer system, comprising: a transfer module adapted to transfer an airplane; a landing gear holder, adapted to firmly grip a landing gear of the airplane; wherein the landing gear holder is pivotally coupled to a structural element of the unmanned transfer system; and a controller, coupled to the transfer module, adapted to control the transfer module in response to a steering induced movement of the landing gear holder.

Abstract: The invention relates to a plane tractor which grips the nose gear of a plane, including: a chassis; wheel modules connected to the chassis, each wheel module including at least one actuator for inducing a vertical movement of the module in relation to the chassis; a gripping platform for gripping the nose gear of a plane, the platform together with the chassis having freedom of movement substantially in circular translation; and a damping and actuating means connecting the platform and the chassis.

Abstract: A device and a related method are disclosed for selectively providing a modified aerodynamic flow over a wing under aerodynamic flight conditions with respect to a respective datum aerodynamic flow over an external wing surface of the wing in the absence of the device under similar aerodynamic flight conditions. The device includes a body configured to be movably mounted to the wing for selective displacement between at least two different positions with respect to the external wing surface and having an external body surface. The device includes a motion inducing arrangement coupled to the body and configured for providing the selective displacement. In each position, the body is in a respective superposed relationship with a respective wing surface portion of the wing external surface and the modified aerodynamic flow includes airflow over the external body surface. A wing and an air vehicle including the device are also disclosed.

Abstract: A variety of refueling devices, systems and methods are disclosed for use in in-flight refueling. In one example one such device is towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and has a boom member with a boom axis. The boom member enables fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during in-flight refueling. The device maintains a desired non-zero angular disposition between the boom axis and a forward direction at least when the refueling device is towed by the tanker aircraft in the forward direction via the fuel hose.