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. 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: An add-on brake system includes a housing accommodating a linear actuator including: an electric motor having a rotor and a stator; a nut arrangement coupled to the rotor; a linear threaded plunger associated having a first end linearly protruding from one end of the arrangement and a second end linearly protruding from an opposite end thereof; an inboard brake pad coupled to the housing; and an outboard brake pad associated with the second end, oriented transverse to the plunger. The plunger has an initial unclamped position in which the second end protrudes to an extent n1 from the other end of the arrangement, yielding a spacing S1 between the inboard and outboard brake pads, and a final clamped position in which the second end protrudes to an extent n2>n1 from the other end of the arrangement, yielding a spacing S2<S1 between the pads.
July 28, 2016
Date of Patent:
May 14, 2019
ISRAEL AEROSPACE INDUSTRIES LTD.
David Elnekave, Yehuda Markus, Zeev Dvorkin, Eran Levy, Michael Barkan
Abstract: Methods are provided for operating an air vehicle having fixed wings. Such methods include the step of providing an operating map of angle of attack associated with the fixed wings with Reynolds number, including conditions of separated flow over the fixed wings and conditions of attached flow over the fixed wings. Such methods also include the step of using the operating map for guidance, causing the air vehicle to operate at least within a low Reynolds numbers range corresponding to the operating map, such as to avoid or minimize risk of causing the air vehicle to operate at conditions of separated flow over the fixed wings.
January 27, 2015
Date of Patent:
May 7, 2019
ISRAEL AEROSPACE INDUSTRIES LTD.
Michael Shepshelovich, Danny Abramov, Yonatan Klein
Abstract: There is provided an inflatable dummy target comprising a chassis wrapped with a sheet. The chassis can be formed by individual inflatable ducts and can comprise at least two ring-shaped ducts interconnected by one or more elongate ducts. The inflatable dummy target can further comprise rigidizing ducts. The inflatable dummy target geometry can be conical, cylindrical, etc. Optionally, the inflatable dummy target can comprise several attached axi-symmetrical sections, wherein each section has a chassis wrapped with a sheet, the chassis formed by individual inflatable ducts. Optionally, the shape of each section can be selected from the group consisting of conical, frustoconical and cylindrical forms.
Abstract: A method of treatment of liquid including supplying liquid to be treated to at least one liquid treatment module having a liquid inlet, a permeate outlet and a brine outlet, monitoring liquid pressure within the at least one liquid treatment module and upon exceedance of a liquid pressure threshold in the at least one liquid treatment module, reducing the liquid pressure in the at least one liquid treatment module by performing at least one of the following functions: opening a liquid pressure reducing valve at the brine outlet, increasing a liquid volume output of a circulation pump which removes brine from the at least one liquid treatment module, equilibrating liquid pressures between a liquid pressure inside the at least one liquid treatment module and inside a liquid feed tank and opening a liquid pressure reducing valve at the liquid inlet.
Abstract: The presently disclosed subject matter includes tracking method and system wherein a succession images is generated at a sensing unit; one or more moving object in the succession of images is identified; an object tag is assigned to at least one of the moving objects to yield in a respective tagged object; responsive to a command received from a control unit indicative of a selected object, identifying a location of the selected object in a latest available captured image, wherein: if the selected object is a moving object, the selected object is identified in the latest available captured image based on a respective object tag; and if the selected object is a stationary object, the selected object is identified using an image or piece thereof comprising the at least one selected object.
Abstract: Two element aerofoils are provided, having an aerofoil chord, a primary element having a first leading edge and a first trailing edge, a secondary element having a second leading edge and a second trailing edge, a gap between the primary element and the secondary element, and an axial overlap between the first trailing edge and the second leading edge. The secondary element is deflectable with respect to the primary element about a fixed hinge point by a flap deflection angle. The secondary element is configured to operate in airbrake mode when deflected by a respective the flap deflection angle corresponding to a design airbrake deflection angle wherein to generate an airbrake drag. In at least some examples, the axial overlap is numerically greater than ?0.5% of the aerofoil chord, at least for the design airbrake deflection angle. Also disclosed are methods for operating air vehicles, and methods for designing two-element aerofoils.
Abstract: The presently disclosed subject matter includes a tracking system and method which for tracking objects by a sensing unit operable to communicate over a communication link with a control center which enables to execute a command generated at the control center with respect to a selected object in an image captured by the sensing unit, notwithstanding a time-delay between a time when the sensing unit acquires the image with the selected object, to a time when the command is received at the sensing unit with respect to the selected object.
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 ice detecting apparatus comprising: a body including at least one ice detector mounted thereon and having an ice detecting surface and a scraping member so mounted relative to said body as to allow their movement one relative to the other and configured for scraping ice from said detecting surface during said movement.
Abstract: Aerofoil accessories are provided, configured for selective attachment to a wing element, the wing element having an outer facing aerofoil surface and being based on at least one datum aerofoil section. Each accessory provides a modified geometric profile to a datum profile of the at least one aerofoil section when attached to the wing element. The accessories are each configured for having a substantially fixed geometric profile with respect to the at least one datum aerofoil section at least whenever said wing element is airborne with the respective accessory attached to the wing element. The modified geometric profile is such as to provide said wing element with the accessory attached thereto with a desired change in performance relative to a datum performance provided by the wing element absent the accessory. A kit is also provided for enhancing performance of a wing element in off-design conditions. A method is also provided for enhancing performance of a wing element in adverse conditions.
September 16, 2009
Date of Patent:
December 4, 2018
ISRAEL AEROSPACE INDUSTRIES LTD.
Michael Shepshelovich, Alex Nagel, Danny Abramov
Abstract: A baggage transfer conveyer unit for mounting over a baggage carousel having a carousel transferring path for transferring a baggage therealong is provided. The conveyor unit comprises a proximal end, a distal end, an upper surface by means of which the baggage is to be transferred from the proximal end to the distal end along a conveyor unit transferring path extending between the ends, a baggage transferring mechanism configured for causing the upper surface to transfer the baggage along the conveyor transferring path; and a baggage diverting mechanism configured for causing a part of the upper surface to divert the baggage from the conveyer unit transferring path along a diverted direction different from that of the conveyor unit transferring path. The baggage transfer conveyer unit is configured to be mounted over the baggage carousel such that the conveyer transferring path is aligned with the carousel transferring path.
Abstract: Systems and methods are disclosed for providing a controlled temperature in a control volume. Such systems include a main chamber (defining the control volume), a mixing chamber and a gasflow source. The mixing chamber is in selective fluid communication with the main chamber, and has at least one mixing chamber inlet, and a ram air inlet for allowing ram airflow at a first temperature to be channeled into the mixing chamber. The gasflow source provides a source gasflow at a greater, second temperature to the mixing chamber. The mixing chamber provides the mixing chamber outflow at a third temperature by selectively allowing the ram airflow and the source gasflow in the mixing chamber to mix therein, or, by selectively allowing the ram airflow in the mixing chamber to flow to the main chamber (in absence of source gasflow). A controller is operative to provide a desired level for the third temperature.
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 refueling airplane converted from a non-refueling airplane having an original tail section and an original tail-strike pitch attitude. The refueling airplane comprises the original tail section and a recess formed therein, both constituting a modified tail section. The recess is configured to at least partially accommodate therewithin a refueling boom. The refueling boom is configured to be mounted to the modified tail section, such that a tail-strike pitch attitude of the refueling airplane, when said refueling boom is mounted thereto, is equal to or greater than the original tail-strike pitch attitude of the non-refueling airplane.
Abstract: The presently disclosed subject matter includes a method, apparatus and computer storage device for reducing dispersion of a rocket caused by jet-stream misalignment, the rocket comprising a rocket engine. Information indicative of a division of total operation time of the rocket engine into a first time period and a second time period is obtained; wherein an impulse which is generated during the first time period is at least approximately the same as an impulse generated during the second time period; a period of time which equals to the first time period starting from time of activation of the rocket engine is measured; upon termination of the period of time, the rocket is rotated around the rocket's longitudinal axis; and the angle of rotation measured; and the rotation is stopped once a 180° rotation is completed.
Abstract: Cargo handling systems and methods for a freight deck of an aircraft are provided, as well as mobile transport apparatus. In at least one example, the system includes a support structure, at least one mobile transport apparatus, and a plurality of locking devices. The support structure is configured for at least partially supporting at least one cargo unit on the support structure, Each mobile transport apparatus is configured for selectively moving over the freight deck to a plurality of locations on the freight deck, for selectively engaging to the at least one cargo unit, for selectively propelling said at least one cargo unit over said freight deck while the apparatus is engaged to the at least one cargo unit, for enabling said at least one cargo unit to be deposited at a desired said location supported on said support structure, and for selectively disengaging from the at least one cargo unit.
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: An interceptor missile comprising: a warhead; a processing unit; one or more sensors configured to obtain at least one reading enabling determination of a passing direction of the interceptor missile with respect to a target; wherein the processing unit is configured to: receive the reading from the sensors; determine a passing direction utilizing the reading; and obtain a required time Tgo for initiating the warhead, utilizing the determined passing direction.
September 12, 2016
June 28, 2018
ISRAEL AEROSPACE INDUSTRIES LTD.
Allan C. KAHANE, Menachem CHAIMOVITZ, Pavel BRUK, Shai VAINGAST
Abstract: A counter-flying object system comprising a sensor array including at least one active sensor configured to detect and track the flying object, and a missile launcher configured to launch an interceptor to intercept the flying object, wherein upon launching of the interceptor, the sensor array is configured to determine the location of the interceptor and send said object and interceptor locations to a control system, the control system being configured to provide mission data to the interceptor based on said object and interceptor locations for guiding the interceptor toward the flying object and activating a fragmentation warhead on or in the vicinity of said flying object when a lethality criteria is met.