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.

Abstract: An aircraft pylon is provided, configured for mounting to the underside of an aircraft wing projecting from a fuselage and for carrying an external payload suspended therefrom. The pylon comprises an attachment mechanism configured for facilitating mounting of the pylon to the aircraft wing, and a carrying arrangement configured for carrying the payload and being pivotally articulated to the attachment mechanism. The pylon is configured to selectively pivot the carrying arrangement about a pylon axis between a vertical position in which it is suspended in a substantially vertical orientation, and a tilted position in which it is tilted toward the fuselage.

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.

Abstract: A hovering aerial vehicle is provided, comprising an airborne unit and an auxiliary unit. The airborne unit is configured to carry the auxiliary unit during flight and comprises a flight system configured to facilitate providing aerodynamic lift to facilitate hovering of the vehicle. The auxiliary unit comprises an electrical power source in electrical communication with the flight system to provide electrical power for its operation. The hovering aerial vehicle further comprises a decoupling system configured to facilitate selectively switching the vehicle between a detached configuration thereof wherein the airborne and auxiliary units are remote from each other, and an attached configuration thereof wherein the airborne and auxiliary units are secured to one another, and to maintain the electrical communication when the vehicle is in its detached configuration.

Abstract: The presently disclosed subject matter includes a computerized method and system for determining miss-distance between platforms. The proposed method and system make use of an electro optic sensor (e.g. camera) mounted on one of the platforms for obtaining additional data which is used for improving the accuracy of positioning data obtained from conventional positioning devices. A navigation error is calculated where the relative position of the two platforms is converted to the camera reference frame. Once the navigation error is available, it can be used to correct a measured miss-distance.

Abstract: A computer-implemented method of controlling an aircraft during autonomous landing. The method includes using a computer for performing the following: applying image processing on an image captured by a camera on board the aircraft while approaching a runway for identifying in the image a touchdown point (TDP) of the runway; calculating a deviation, in image parameters, of the TDP relative to the center of the image; converting the deviation in image parameters to angular and distance deviation values based on predefined ratios; calculating an offset of the aircraft's position relative to a landing corridor ending at the identified TDP based on the calculated angular and distance deviation; and transmitting the calculated offset to an aircraft control system configured to provide instructions for controlling the aircraft; wherein the offset is used for controlling the aircraft for guiding the aircraft towards the landing corridor to enable landing.

Abstract: A method of calibrating a levelling offset meter (LOM) for calculating the angular offset between a plane parallel to the LOM and a predetermined reference plane, the LOM comprises a bull's eye spirit level having a bubble and a processor coupled to an image, comprising: capturing, by the imager, a plurality of images of the spirit level associated with a respective plurality of known angular offsets; calculating in respect of each image a pixel distance from the bubble center to a predetermined zero offset pixel, thereby obtaining a plurality of pixel distances, each pixel distance associated with a known angular offset; fitting a function to a plurality of pairs of values, each pair of values comprising a pixel distance and its associated known angular offset; and storing the function in a memory.

Abstract: The presently disclosed subject matter includes a UAV surveillance system and method which enables quick and convenient activation of an on-board radar (e.g., in SAR or GMTI mode) without having predefined suitable flight instructions. It enables ad-hoc operation of radar data acquisition devices allowing to switch from EO data acquisition to radar data acquisition or activate a radar side-by-side with an EO sensing device.

Abstract: There is provided a method for converting a turbofan engine, including the step of providing a turbofan engine and the step of converting the turbofan engine to provide a converted turbofan engine. The turbofan engine includes a core engine (including at least one high pressure spool assembly and a combustion chamber), and an unmodified fan configured for providing at least a bypass flow bypassing the core engine, the fan being mechanically coupled to a low pressure turbine that is in turn driven by the core engine.

Abstract: The presently disclosed subject matter includes a computerized method and system for determining miss-distance between platforms. The proposed method and system make use of an electro optic sensor (e.g. camera) mounted on one of the platforms for obtaining additional data which is used for improving the accuracy of positioning data obtained from conventional positioning devices. A navigation error is calculated where the relative position of the two platforms is converted to the camera reference frame. Once the navigation error is available, it can be used to correct a measured miss-distance.

Abstract: A method of treatment of liquid in a liquid treatment system comprising: at least one liquid treatment module including at least one membrane and having a feed liquid inlet at a feed side of said at least one membrane, a permeate outlet at a permeate side of said at least one membrane, and a concentrate outlet at a brine side of said at least one membrane; a high pressure pump operative for pressurizing feed liquid to be received at said feed liquid inlet; and a system controller for controlling operation of the system including providing instructions to operate said high pressure pump in one of at least two operation modes including: a first mode in which the high pressure pump maintains a fixed flow rate of the feed liquid at said feed liquid inlet or of a permeate liquid at said permeate outlet, while energy consumption of said high pressure pump being a function of variations of a first operational parameter measured in the system and indicative of salinity of liquid within said at least one liquid treatm

Abstract: The disclosed subject matter includes, an airborne data library onboard an airborne platform, configured for automatic management of situation awareness data (SAD), the airborne data library comprising an onboard data management system; the on-board data management system comprises a data management unit and an onboard data-repository; the data management unit being operatively connectible to at least one computer processor and configured to: establish a communication link with at least one situation awareness data (SAD) source; obtain situation awareness data from the at least one SAD source; process the SAD based on data management logic being accessible to the data management unit.

Abstract: An aircraft engine system configured with a high pressure stage turbocharger assembly and a supplemental stage turbocharger assembly disposed in series with respect to said high pressure stage turbocharger, wherein the supplemental stage turbocharger assembly provides a compressor unit of the high pressure stage turbocharger with substantially constant critical altitude pressure input.

Abstract: The presently disclosed subject matter includes a camera system for aerial photography applications which can be mounted on an aircraft and be operated for obtaining images of a surveyed area. The proposed camera system comprises a camera control unit operatively connected to a camera supported by a pivotal supporting device such as a gimbal assembly. The camera is continuously moved along a scanning line without stopping and is operated to capture images in a certain frame rate, this is carried out by measuring as well as regulating the angular velocity of the camera to adapt the pictured and the non-pictures zones over the scanning line.

Abstract: A computer-implemented method for identifying clouds in a digital image, comprising pixels, of a scene, the method comprising quantifying pixel-level characteristic/s in each of a multiplicity of pixels within a digital image of a scene; comparing function/s of the pixel-level characteristic/s to threshold/s thereby to generate comparison result/s; and using a controller for generating an output identifying clouds in the digital image, including identifying presence of cloudiness at at least one first pixel in the digital image, at least partly because the at least one comparison result indicates that the first pixel falls below the threshold/s, and identifying absence of cloudiness at at least one second pixel in the digital image, at least partly because the at least one comparison result indicates that the second pixel exceeds the threshold/s.

Abstract: An Identification Friend or Foe (IFF) interrogation system and method adapted for: transmitting RF broadcast signal to be received by complementary transponder(s) of the IFF system being within the interrogation range and thereby arm the complementary transponders for sensing laser beam illumination; receiving an RF response signal from the complementary transponder(s); operating a laser activation interface module, which is configured for interfacing an external laser transmitter, to determine activation of transmission of an interrogating laser beam by the external laser transmitted; and receiving and processing RF signals to identify therein RF response signal(s), which are transmitted by the complementary IFF transponder(s) in response to detection of the trans mitted laser beam.

Abstract: A polarimetric phase array radar system (PPARS) for determination of parameters of a target and a method of operating the PPARS are described. The PPARS includes an array having transceiver elements configured to transmit transmitting signal components of a dual-polarization signal having either a single type polarization or simultaneously two types of polarization. The array also configured to receive a receiving signal component having a single type of polarization. In transmitting mode, the transceiver elements are operative to transmit a signal component having one or two types of polarization. In receiving mode, the transceiver elements are divided into at least two sub-arrays.

Abstract: A gradiometer system including one or more magnetic sensor(s) is disclosed. The gradiometer includes an actuation module connectable to the magnetic sensor(s) to vary one or more sensing positions at which a magnetic field is sensed thereby. The one or more sensing positions are varied according to a certain displacement function indicating a predetermined displacement between the sensing positions as a function of time.

Abstract: A projectile is disclosed, having: a longitudinal axis, a steering assembly, a shell body, an attitude control system, a despin module, an electromagnetic receiver and/or emitter system, and a controller. The attitude control system includes a ram air inlet in selective open fluid communication with an exhaust assembly, which includes a plurality of exhaust outlets to selectively generate each of a plurality of thrust jets from a ram air inflow provided by the ram air inlet, each thrust jet being selectively controllable via the controller. The despin module is configured for selectively de-spinning the steering assembly with respect to the shell body about the longitudinal axis. The electromagnetic receiver and/or emitter system is configured for receiving and/or emitting electromagnetic energy, and for cooperating with the controller for operating the exhaust assembly to thereby selectively provide steering control moments. Systems and methods for steering the projectile are also disclosed.

Abstract: The presently disclosed subject matter includes a computerized method and system for determining miss-distance between platforms. The proposed method and system make use of an electro optic sensor (e.g. camera) mounted on one of the platforms for obtaining additional data which is used for improving the accuracy of positioning data obtained from conventional positioning devices. A navigation error is calculated where the relative position of the two platforms is converted to the camera reference frame. Once the navigation error is available, it can be used to correct a measured miss-distance.