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公开(公告)号：US11518495B2
公开(公告)日：2022-12-06
申请号：US16981499
申请日：2019-05-02
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Elie Koskas , Victor Weissberg
Abstract: A composite structural member including at least one first flange element made from a first composite material, and at least one first web element made from a second composite material. The at least one first web element is connected to at least one first flange element in a non-coplanar manner along a corresponding mutual first edge via a first corner element made from a third composite material, the mutual first edge extending along a first direction. The third composite material includes a corresponding first plurality of third composite material first fibers and a corresponding second plurality of third composite material second fibers embedded in a corresponding third composite material matrix in a non-parallel orientation with respect to the third composite material first fibers, wherein the third composite material first fibers are nominally orthogonal to the mutual first edge or to the first direction.
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公开(公告)号：US11493344B2
公开(公告)日：2022-11-08
申请号：US16635245
申请日：2018-07-30
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Michael Maidanik , Assaf Nachum , Miki Livne
Abstract: The presently disclosed subject matter includes a method and system directed for calculating azimuth of an airborne platform during flight based on IMU measurements, without using GNSS data, gyrocompassing or magnetometers operating on the ground for determining the azimuth.
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公开(公告)号：US11434025B2
公开(公告)日：2022-09-06
申请号：US16964307
申请日：2019-01-15
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Erez Yacoby
Abstract: A space vehicle comprising an optical system having a field of view, the optical system comprising at least two optical elements spaced from one another along an optical axis, thereby defining an interior cavity; at least one control system comprising at least one physical element configured for performing function(s) for enabling operation of the vehicle; and at least one holding assembly for holding the at least one control system and comprising a folding mechanism configured to move between a folded position corresponding to an inoperative mode of the optical system, and a deployed position corresponding to an operative mode of the optical system, such that in the folded position, the control system is at least partially located in the interior cavity for stowage, and in the deployed position, the control system is located outside the interior cavity and outside the field of view of the optical system, allowing operation of the optical system.
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公开(公告)号：US11373542B2
公开(公告)日：2022-06-28
申请号：US16961546
申请日：2019-01-10
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Moshe Sabato
Abstract: The presently disclosed subject matter includes an active proximity system (APS) mountable on an unmanned autonomous vehicle (UxV), the APS comprising: one or more proximity sensors and a processing circuitry; the one or more proximity sensors are configured to sense one or more proximity signals, each of the signals is indicative of the presence of a respective emitter in proximity to the UxV; the processing circuitry is configured, responsive to a sensed proximity signal, to repeatedly: generate maneuvering instructions dedicated for causing the UxV to move and increase the distance between the UxV and the respective emitter; and then generate maneuvering instructions dedicated for causing the UxV to move and decrease the distance between the UxV and the respective emitter; and thereby maintain the UxV within a certain range from the respective emitter defined by the sensed proximity signal.
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公开(公告)号：US11329398B2
公开(公告)日：2022-05-10
申请号：US16620787
申请日：2018-06-13
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Vladimir Rojanski
Abstract: An antenna device is presented. The antenna device comprises: a conformal antenna body which has a desired geometry corresponding to a front portion of a platform on which the antenna device is to be mounted, and an antenna unit carried by the antenna body. The antenna unit comprises at least one phased array of antenna elements. The antenna elements of each array are arranged in a spaced-apart relationship in a closed loop path along a circumference of the antenna body having a desired geometry corresponding to a front portion of platform on which the antenna unit is to be mounted. Each of the antenna elements is configured as an end-fire antenna element capable of emitting linearly polarized radiation, the array of the antenna elements being thereby operable as a forward looking end-fire antenna array, enabling electronic steering of an antenna beam by controllably modifying phases of the antenna elements of each array.
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公开(公告)号：US11220324B2
公开(公告)日：2022-01-11
申请号：US16478221
申请日：2018-02-01
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Shahar Bar Hillel , Saar Shragai
Abstract: Apparatuses for a projectile are provided, the projectile configured for weapons band launching, examples of the apparatus comprising a body, an inflation system and external walls. The body is inflatable by the inflation system, from a deflated configuration having a first volume to an inflated configuration having a second volume, greater than the first volume. The external walls are deployable from an undeployed configuration to a deployed configuration responsive to the body being inflated. In the undeployed configuration and at an operating airspeed, the center of pressure is located at a first position with respect to the projectile. In the deployed configuration the external walls provide a deployed external surface geometry exposed to an airflow corresponding to the operating airspeed, such that the center of pressure is located at a second position with respect to the projectile, different from the first position.
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公开(公告)号：US11187507B2
公开(公告)日：2021-11-30
申请号：US16820238
申请日：2020-03-16
Applicant: Israel Aerospace Industries Ltd.
Inventor： Jacob Rovinsky
Abstract: A fragmentation warhead is provided, capable of being mounted in a carrier vehicle, the warhead having a longitudinal axis. In at least one example the warhead includes a shell that extends along the longitudinal axis. The shell includes a fixed shell portion and a fragmentation portion, and defines therebetween a cavity for accommodating therein an explosive charge. The fragmentation portion includes at least one set of serially adjacent fragments in correspondingly serially contiguous relationship in the fragmentation portion and in generally helical relationship with respect to the longitudinal axis. A corresponding carrier vehicle and a corresponding missile are also provided.
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公开(公告)号：US11167860B2
公开(公告)日：2021-11-09
申请号：US16537074
申请日：2019-08-09
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Ohad Rix , Joshua Gur , Michael Litvak , Elie Koskas
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.
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公开(公告)号：US11126201B2
公开(公告)日：2021-09-21
申请号：US16334418
申请日：2017-12-18
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Ohad Rozenberg , Haim Somech
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.
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公开(公告)号：US10965769B2
公开(公告)日：2021-03-30
申请号：US15525428
申请日：2015-11-10
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Moshe Sabato
IPC: H04L29/08 , G06F16/23 , G06F16/9537 , H04B7/185
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.
