Abstract: There are provided a method of evaluating an area located behind a structure and a system thereof. The system includes: at least one source of electro-magnetic radiation adapted to illuminate a structure portion and to illuminate a area portion via openings formed between elements of the structure while a relative movement is introduced between the structure and the system; multiple detectors adapted to detect electro-magnetic radiation returned from the structure portion and from the area portion; a computing unit adapted to: (i) generate, in response to the detected electro-magnetic radiation, a simplified representation the area portion; and (ii) evaluate the area portion in response to a relationship between the simplified representation of the area portion and a reference simplified representation of the area portion.

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: Apparatus and method are provided for controlling a vehicle in motion through a fluid medium. A manipulable flare assembly is mounted to a load bearing structure, the structure being configured for mounting to the vehicle. An actuating mechanism has a rotational member operably associated with the flare assembly, the actuating mechanism being configured for selectively providing relative rotation between the rotational member and the load bearing structure. The actuating mechanism is configured for manipulating the flare assembly responsive to selective relative rotation between the rotational member and the load bearing structure. A vehicle is also provided incorporating the apparatus.

Abstract: A water desalination system including at least one reverse osmosis desalination unit, including at least one reverse osmosis membrane and having a saline water inlet at a feed side of the at least one reverse osmosis membrane and a permeate outlet at a permeate side of the at least one reverse osmosis membrane, and an intermittent cleaning control subsystem operative to provide intermittent cleaning of the at least one reverse osmosis membrane by at least one of narrowing or closing the permeate outlet, thereby causing an increase of pressure of the permeate at the permeate side of the at least one reverse osmosis and reducing the feed pressure, without significantly increasing the permeate pressure, thereby causing permeate to flow from the permeate side to the feed side of a membrane and flushing foulants to a location outside of the desalination unit.

Abstract: A vehicle for towing an airplane by receiving thereupon a nose landing gear of the airplane having an airplane longitudinal axis. The vehicle having a vehicle longitudinal axis and is configured to tow the airplane along a straight or curved path and comprises a controller for directing its operation, including maintaining the vehicle's in-phase position in which the vehicle longitudinal axis is parallel to the airplane longitudinal axis.

Abstract: There is provided a system for detecting distant seaborne objects by an airborne vehicle, including a seeker head having an axis in the direction of flight, a sensor mounted on the seeker's head, the sensor being operative to transmit towards the sea surface a laser radiation beam of selected wavelength and to receive from the sea water surface radiation reflected from the sea water surface and from a seaborne object, and a computing unit for differentiating between the reflection received from the sea water surface and from the seaborne object. A method for detecting distant seaborne objects by an airborne vehicle is also provided.

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

Abstract: A towbarless airplane tug comprising: a chassis mounted on a plurality of tug wheels, at least some of said plurality of tug wheels being steerable tug wheels; an airplane wheel support assembly, mounted on said chassis, for supporting rotatable wheels of a nose landing gear of an airplane; at least one tug wheel driver operative to drive said plurality of tug wheels in rotation to provide displacement of said chassis; and at least one tug controller operative to control speed of said tug, said at least one tug controller employing at least one feedback loop utilizing a mapping of speed limits along a travel path traversed by said tug and said airplane at said airport as well as an indication of the instantaneous location of said tug and said airplane along a travel path.

Abstract: A computerized system for monitoring physical data for anomalies, which physical data are predictable given predetermined information, the system comprising a predetermined information data point generator operative to compute a sequence of model data points which the physical data, given predetermined information, can be expected to duplicate at each of a corresponding sequence of temporal sampling points; a wayward point monitor including a processor operative for monitoring the physical data including identifying wayward points within said physical data that are incongruous with the predetermined information; and an anomalous episode-prompted alarm generator operative for identifying anomalous episodes, each including a cluster of wayward points satisfying predefined anomalous episode-defining criteria and generating an alarm for each anomalous episode identified.

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: Projectile assembly apparatus comprising a projectile and a projectile head-protecting element surrounding at least a portion of the projectile and operative to separate from the projectile only as the projectile is launched, the projectile head-protecting element including a separation prevention device operative to prevent said projectile head-protecting element from separating from said projectile until a launch-indicative event has occurred.

Abstract: A projectile (100) is provided for operating at least in a launch phase and in a post-launch phase. The projectile includes a projectile body (10), a projectile head (50), and a support structure (80). The projectile head is non-rigidly mounted to the projectile body via a joint structure (70). The support structure is configured for selectively supporting the projectile head with respect to the projectile body in a load bearing relationship independently of the joint structure during at least a portion of the launch phase, and for selectively terminating the support during at least a portion of the post-launch phase. A method for operating a projectile and a method for retrofitting a projectile are also provided.

Abstract: Disclosed a towbarless airplane tug and method of operating thereof.

Abstract: In an embodiment, a towbarless airplane tug configured for receiving a landing gear of an airplane and towing the airplane thereby at an actual speed is disclosed. The towbarless airplane tug includes a chassis configured for receiving thereon at least a portion of the landing gear, and a propulsion arrangement configured to move the towbarless airplane tug in a direction along a trajectory. The towbarless airplane tug further includes a controller configured to compare between the actual speed of the towbarless airplane tug, when towing the airplane, and a predetermined desired speed thereof, and to direct the propulsion arrangement to maintain the actual speed of the towbarless airplane tug if: the actual speed is lower than the desired speed, and the actual speed was maintained within a predefined speed range during a predefined period that preceded the comparing.

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 payload including a gimbal assembly and gyro assembly that includes a gyro assembly control associated with the gyro assembly and operable to trigger the gyro assembly to obtain deviation measurements and process the measurements in a first dynamic range for stabilizing the payload utilizing the gimbal assembly. The gyro assembly control is operable to trigger the gyro assembly to obtain instantaneous measurements and process the measurements in a second dynamic range having different sensitivity than the first dynamic range, for finding deviation of the payload from the magnetic north of the earth.

Abstract: An airplane tug for receiving a landing gear of an airplane. Tug comprises a chassis for receiving the landing gear, a propulsion arrangement for moving tug, force sensor(s) for measuring a force exerted by the chassis on the gear due to a speed differential between tug and airplane, and a controller for altering movement parameter(s) of tug for maintaining the force below a value. Propulsion arrangement comprises a variable angle swash plate hydraulic pump coupled to a variable angle swash plate hydraulic motor and to a bypass path valve such that fluid circulates between the pump and motor to activate the arrangement to increase the speed and/or traction force when bypass path is in a closed state, and the fluid circulates across the motor via the valve to reduce a rotational speed and/or traction force of the tug when the path is in an opened state.

Abstract: A method and system are presented for use in determination of the orientation of an aerospace platform with respect to a first rotation axis. A direction of a rotation rate vector of said aerospace platform within a lateral plane intersecting with said first rotation axis is measured and the measured data is analyzed to determine an orientation angle of said aerospace platform about said first rotation axis. While the aerospace platform is in a predetermined-dynamic state movement, a certain direction is determined by measuring a direction of the rotation rate of the aerospace platform within said lateral plane by a sensor assembly mounted on said platform and including at least one rotation rate sensor. An orientation of the platform with respect to said first axis is determined by determining a relation between said certain direction and said known direction within said external reference frame.

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: A method for controlling in-flight refueling of a receiver aircraft having a fuel receptacle, comprising: automatically steering a refueling device to an engagement enabling position, including: repeatedly determining a spatial disposition of the refueling device with respect to the receiver aircraft, the refueling device being capable of engaging and refueling the receiver aircraft via a boom member, when the device arrives to the engagement enabling position at which the boom member is in a predetermined spaced and spatial relationship with respect to the fuel receptacle of the receiver aircraft; repeatedly calculating steering commands based at least on the repeatedly determined spatial dispositions and characteristics of a spatial control system of the refueling device; sending the steering commands to the spatial control system; whereby at the engagement enabling position, the boom member of the refueling device is capable of engaging with the fuel receptacle to enable refueling of the receiver aircraft.