Abstract: A method of transferring a plurality of containers to storage is provided, the method comprises providing at least one multi-level structure (12) with an elevator (22) configured to receive and transport one or more containers thereupon and being configured to ascend and descend to a predetermined level (18a), each of the levels (18a) comprising a plurality of bays (24) being sized to receive and store therein one of the containers; providing a plurality of unmanned autonomous guided vehicles (AGV) configured to perform front/back and sideways movements and to receive a container thereupon; receiving each of the containers on a receiving AGV (rAGV) of the AGVs; and positioning the rAGV with the container received thereby in a target bay (24) on a target level (18a) of the structure (12).

Abstract: The present invention concerns a composite article comprising a plurality of layers, wherein at least one of the layers is a defective polymeric layer. The defective polymeric layer has at least one artificial defect, in the form of a volume of air confined by walls made of said defective polymeric layer, and by layers adjacent thereto. The invention further provides the use of a composite article for calibrating equipment and a method for making such a composite article.

Abstract: A side-pumped, diode-pumped solid-state laser cavity includes a conductively cooled housing having an opening for pump radiation from a diode array in close proximity to a laser rod. The pump light is absorbed by the rod and excites the laser ions. The cavity includes a thin, diffuse reflector encircling the rod, having a shaped opening for the collection and redirection of the pump light into the rod, and a good heat conductor as the heat sink and heat conductor. A split heat sink inhibits the flow of heat from the pump diodes into the laser rod, and pre-formed air spacings are designed to provide uniform temperature distribution around the laser rod.

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: 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; (h) 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 system is provided for guarding a perimeter, including a control center, a launch system, a controller and a communication system. The control center is configured for generating a control signal responsive to receiving infiltration information of an actual or suspected infiltration at a target zone associated with the perimeter by one or more infiltration agents. The launch system is configured for deploying one or more ready-to-launch UAV's to the target zone responsive to receiving the control signal from the control center. The controller is configured for operating the launched UAV(s) to home onto at least one such infiltration agent. The controller is also configured for identifying the nature of the infiltration agent or the nature of infiltration; and/or for tracking the infiltration agent via the UAV(s).

Abstract: A method for transferring airplanes and an unmanned airplane transfer system. The airplane transferring system includes: receiving a transfer signal responsive of a movement of an airplane control component; and transferring an airplane, by an unmanned airplane transfer system, in response to the transfer signal.

Abstract: An extendable sway brace for a rack for an airborne payload. The sway brace is extendable. A mechanism for extending the sway brace includes means for preventing extension of the sway brace when the pressure exerted by the brace on a payload reaches a predetermined pressure. The means for preventing extension of the brace may include, for example, one or more pre-loaded springs. In this case, extension of the brace is prevented when the springs are compressed by a predetermined amount. The invention also provides a rack for an airborne payload comprising a sway brace of the invention.

Abstract: A hybrid transonic-subsonic airfoil is provided that combines subsonic and transonic features for achieving simultaneously acceptable aerodynamic characteristics at low subsonic and high transonic Mach numbers.

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: In embodiments, a system and method for providing propulsion and control to an air vehicle, and for operating the vehicle, include at least three propulsion units that provide vertical thrust for vectored thrust flight, in which at least one or two of the propulsion units also provide thrust for vectored thrust cruising or aerodynamic flight by suitably tilting the respective propulsion units for changing the thrust vector thereof. At the same time, the three or more propulsion units are operated to generate controlling moments to the air vehicle about three orthogonal axes, pitch, roll and yaw, during vectored thrust flight (hover, cruising, etc.) or during aerodynamic flight for controlling the vehicle.

Abstract: There is provided an interception system that employs miniature kill vehicles. According to certain embodiments of the invention, a small kill-vehicle (KV) accommodated within an interceptor missile together with additional at least one KV, each KV is equipped with an image acquisition sensor operable in the visible or near IR range, and adapted to be launched from the interceptor missile during exo-atmospheric flight and utilizing said sensor for tracking and homing at least one Re-entry Vehicle (RV) of a Ballistic Missile (BM).

Abstract: An optical imaging system is provided for an airborne platform or the like, including an image acquisition unit having an optical axis and configured for providing images in a direction along said axis, the image acquisition unit being mounted to a pointing mechanism configured for selectively pointing said optical axis in a desired direction. The system also has an optical shield configured for shielding said image acquisition unit from receiving undesired electromagnetic radiation from at least one direction different from said desired direction.

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: An aircraft arrangement for Mini or Micro UAV comprising a fore wing (14) and an aft wing (12) in tandem closed-coupled arrangement. The aft wing (12) has side panels (18) and control surfaces (19), and tapered planform with positive sweep, while the fore wing (14) has non-positive trailing edge sweep. The fore wing (14) and the aft wing (12) are disposed at different height, and the aircraft arrangement has no other wings or tail arrangements.

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: The invention relates to an aircraft, and a method for operating an aircraft, the aircraft having a longitudinally unstable configuration and swept wings, the swept wings being based on aerofoils having a leading edge and configured for preventing attachment line transition in conditions of laminar flow over the swept wing for at least a predetermined first range of lift coefficients at a second range of Reynolds numbers. The invention also relates to an aerofoil, and to a method for providing an aerofoil, the airfoil being configured for a thick-sectioned subsonic/transonic swept wing, having a curved leading edge, a trailing edge, a thickness dimension and a chord dimension, wherein the leading edge comprises a leading edge curvature associated with a leading edge radius that is configured for preventing attachment line transition in conditions of laminar flow over the swept wing.

Abstract: A slotted aerofoil configuration is provided in which the leading element thereof is contoured to provide mild stall characteristics. A wing based partially or fully on such an aerofoil, an air vehicle including such wings, and a method for designing an aerofoil are also disclosed.

Abstract: An air vehicle is provided, including a body having a longitudinal axis, a wing arrangement rotatably mounted to the body with respect to the longitudinal axis, a direction control arrangement for controlling the direction of motion of the body, and an actuation mechanism operable for selectively and controllably rotating the wing arrangement with respect to the body through at least a desired first angular displacement about the longitudinal axis. Methods for operating air vehicles are also provided.

Abstract: A steering system for use in a traveling guided flying apparatus (10) and method for driving the steering system are provided. The system includes an outer housing (111), an inner housing (113) and a support fins (112) extending inwardly from the outer housing (111) and holding the inner housing (113) thereon. The outer housing (111) and the inner housing (113) define a ram air inlet (114) at a nose of the forward portion (11), an annular inlet air passage (115), an annular pressure chamber (116), and an outlet air passage (125). The steering system further includes exhaust outlets (120) arranged in the outer housing and separately controlled valves (124) mounted at the exhaust outlets (120) configured to vary the flow of escaping air through the exhaust outlets (120). The steering system also includes a target seeker (121), one or more pressure sensors (119) mounted in the pressure chamber (116) and a control unit (122) for controlling flight of the guided projectile (10).