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1. 发明授权

US11932386B2 Air vehicle and method of operation of air vehicle 有权
公开(公告)号：US11932386B2
公开(公告)日：2024-03-19
申请号：US17296427
申请日：2019-11-20
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Ehud Baharav , Avner Volovick
IPC分类号： B64C29/00 , B64C39/04
CPC分类号： B64C29/0033 , B64C29/0025 , B64C39/04
摘要： An air vehicle has an airframe, aerodynamic lift-generating wings, and a propulsion system. The propulsion system provides propulsion to the air vehicle in powered aerodynamic flight mode and in vectored flight mode, and stability and control in vectored flight mode. The propulsion system includes a first set of non-pivotable first propulsion units, arranged in polygonal arrangement with respect to the airframe, enclosing the air vehicle center of gravity, providing a fixed vertical thrust vector and an aggregate vertical thrust sufficient for enabling vectored flight mode. The propulsion system includes a second set of pivotable second propulsion units, arranged in spaced relationship with respect to the center of gravity, and provide vectored control moments to the air vehicle in three rotational degrees of freedom. The second propulsion units enable angular displacement of the respective thrust vectors at least between a respective vertical position and a respective horizontal position, and provide at least an aggregate horizontal thrust sufficient for providing powered aerodynamic flight mode.

2. 发明授权

US11919655B2 System and method for refueling air vehicles 有权
公开(公告)号：US11919655B2
公开(公告)日：2024-03-05
申请号：US16621573
申请日：2018-06-17
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Ido Meidad
IPC分类号： B64D39/02 , B64C39/02 , B64U50/34
CPC分类号： B64D39/02 , B64C39/024 , B64U50/34
摘要： A method for controlling maneuver of a refueling device, that includes: a refueling device is attached by a hose to a component of an aircraft. That component maintains a reference force on the hose. The desired position and current position of the refueling device are obtained. A determination is made, based on the current and desired positions of the refueling device, whether to extend or retract the hose. Depending on the determination, a command is sent for adjusting force generating arrangements that are attached to the refueling device. This causes the component to detect a changed force and to maintain the reference force on the hose. The distance between the fueling device and the aircraft is thereby changed.

3. 发明授权

US11902666B2 Systems and methods of image acquisition 有权
公开(公告)号：US11902666B2
公开(公告)日：2024-02-13
申请号：US17775450
申请日：2020-09-30
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Erez Yacoby
IPC分类号： H04N23/695 , H04N23/66
CPC分类号： H04N23/695 , H04N23/66
摘要： An imaging method which comprises, while a line of sight of a camera is maintained fixedly oriented towards a target, controlling the camera to acquire an image by a sensor located at a current position relative to the camera, sending a command to an actuator of the sensor, for inducing a motion of the sensor relative to the camera along at least one direction, from the current position to a new position, controlling the camera to acquire an image by each of the pixel bands of the sensor, wherein motion of the sensor is performed during a first period of time, and the sensor is retained stationary at the new position during a second period of time, wherein acquisition of the image is performed during a third period of time, wherein a majority of the third period of time is within the second period of time.

4. 发明授权

US11834192B2 Devices, systems and methods for refueling air vehicles 有权
公开(公告)号：US11834192B2
公开(公告)日：2023-12-05
申请号：US17497514
申请日：2021-10-08
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Ohad Rix , Joshua Gur , Michael Litvak , Elie Koskas
IPC分类号： B64D39/06 , B64D39/00 , B64D39/04 , B64D3/00 , G05D1/00 , G05D1/10
CPC分类号： B64D39/06 , B64D3/00 , B64D39/00 , B64D39/04 , G05D1/0094 , G05D1/101
摘要： 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.

5. 发明公开

US20230343224A1 ACCESS-DOOR-INTEGRATED WIRELESS INTERCOM SYSTEM 审中-公开
公开(公告)号：US20230343224A1
公开(公告)日：2023-10-26
申请号：US17913932
申请日：2021-03-09
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Nimrod GEORGE , Ran BRAIER
IPC分类号： G08G5/00
CPC分类号： G08G5/0013
摘要： A system of wireless communication between a ground intercom of an aircraft and external systems comprises: a) an access door of a ground intercom access compartment of the aircraft, the door configured to be fixed to the compartment; b) a wireless ground intercom communications processing circuitry comprised in the door; and c) antenna(s) comprised in the door. The compartment comprises a ground intercom access panel, which comprises socket(s). The processing circuitry is operatively connectable to the ground intercom of the aircraft, via the panel, and to the antenna(s Plug(s) are connected to the processing circuitry, and are configured for plugging into the socket(s). This thereby enables retrofit of the system on an existing aircraft, by means of plugging the plug(s) into socket(s) of an existing ground intercom access panel of the aircraft. The system selectively provides wireless communication between the aircraft's ground intercom and the external system(s).

6. 发明授权

US11718406B2 Cockpit of an airplane and method of operating an airplane 有权
公开(公告)号：US11718406B2
公开(公告)日：2023-08-08
申请号：US17635868
申请日：2020-09-24
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： David Shavit
IPC分类号： B64D11/06 , B64D11/00
CPC分类号： B64D11/0689 , B64D11/0601 , B64D11/0641 , B64D2011/0076
摘要： A cockpit for an airplane having, in a plan view, an aft direction, a central longitudinal axis parallel to the aft direction and a rear axis perpendicular to the central longitudinal axis. The cockpit as seen in the plan view comprises: a first seat having a first seating surface with a first seat rear edge passing through an intersection between the longitudinal and rear axes, the first seat being disposed within the cockpit and configured so as to allow a pilot sitting on the first seating surface to perform pre-determined primary pilot functions; and a second seat having a second seating surface with a second seat rear edge. The second seat has: an operational state, in which the second seat is disposed within the cockpit and configured so as to allow operational seating of a pilot on the second seating surface to perform pre-determined secondary pilot functions, the second seat rear edge being at an operational distance from the rear axis; and at least one non-operational state, in which the operational seating of the secondary pilot is disabled, the at least one non-operational state comprising a resting state in which the footprint of the second seat in plan view is longer in at least one dimension than the footprint of the second seat in the operational state, allowing a lying-down position of the secondary pilot.

7. 发明公开

US20230211902A1 DEPLOYABLE WING SYSTEM FOR AIR VEHICLE 审中-公开
公开(公告)号：US20230211902A1
公开(公告)日：2023-07-06
申请号：US18000960
申请日：2021-06-24
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Danny Abramov , Yoav Heichal
IPC分类号： B64U30/12 , B64C3/56 , B64U70/70
CPC分类号： B64U30/12 , B64C3/56 , B64U70/70
摘要： A wing system is provided for an air vehicle, the air vehicle having a fuselage including a fuselage longitudinal axis. The wing system includes a set of wings, configured for transitioning between a stowed configuration and a deployed configuration. The set of wings includes a first said wing having a first wing tip, a first wing longitudinal axis, and a first pivot axis; and a second said wing having a second wing tip, a second wing longitudinal axis, and a second pivot axis. The first pivot axis and the second pivot axis are non-coaxial. In the stowed configuration, the first wing and the second wing are in overlying relationship such that at least a majority of a pressure surface of one wing is facing a suction surface of the other wing, and the first wing tip is spaced from the second wing tip by a first lateral spacing. In the deployed configuration, the first wing is oriented with respect to the second wing such that the first wing tip is spaced from the second wing tip by a second lateral spacing greater than the first lateral spacing. The transitioning includes a pivoting operation, including: pivoting the first wing about the first pivot axis between the stowed configuration and the deployed configuration; and, pivoting the second wing about the second pivot axis between the stowed configuration and the deployed configuration.

8. 发明公开

US20230184876A1 POSITIONING USING SATCOM 审中-公开
公开(公告)号：US20230184876A1
公开(公告)日：2023-06-15
申请号：US17919889
申请日：2021-05-18
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Ohad Rozenberg , Menachem Saidov
IPC分类号： G01S5/02 , G01S13/46
CPC分类号： G01S5/02585 , G01S13/46 , G01S2013/468
摘要： According to one aspect of the presently disclosed subject there is provided a system implemented in a mobile carrier for determining a position of the mobile carrier by using a processing and memory circuitry (PMC) and a satellite communications on the move (SOTM) antenna system, being configured to maintain a communications link from a satellite communications (SATCOM) having a spatial position. The system is configured to obtain data indicative of the spatial position of the SATCOM, the estimated altitude of the mobile carrier and the direction of the antenna towards the SATCOM spatial position and to determine the position of the mobile carrier.

9. 发明授权

US11623771B2 Nano-satellite 有权
公开(公告)号：US11623771B2
公开(公告)日：2023-04-11
申请号：US17044883
申请日：2019-04-15
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Daniel Davies , Tal Mines , Eli Matza
IPC分类号： B64G1/64 , B64G1/10 , B64G1/44 , B64G1/66
摘要： A satellite is provided, configured for stacking with another similarly designed satellite and to facilitate separation thereof. The satellite comprises a housing for carrying functional components, having a plurality of pairing arrangements and a separation arrangement. Each of the pairing arrangements comprises a post extending perpendicularly to a horizontal plane of the housing, and first and second guide members. First guide members of the satellite are configured to couple with second guide members of the other satellite when stacked therewith. The separation arrangement comprises a thrust element configured to impart an ejection force to facilitate the separation, and a release assembly configured to selectively facilitate allowing the ejection force to propel one of the satellites, thereby initiating the separation. The first guide member of the satellite cooperates with the second guide member of the other satellite to deflect it from the horizontal plane during separation.

10. 发明授权

US11619953B2 Three dimensional aircraft autonomous navigation under constraints 有权
公开(公告)号：US11619953B2
公开(公告)日：2023-04-04
申请号：US16892729
申请日：2020-06-04
申请人： ISRAEL AEROSPACE INDUSTRIES LTD.
发明人： Ohad Rozenberg , Erez Avrahamov
IPC分类号： G05D1/10 , B64C39/02 , G08G5/00 , G08G5/02
摘要： According to the presently discloses subject matter, a flight path is autonomously generated (e.g. in response to an unexpected need to land the aircraft) leading the aircraft from its current position towards a target destination (e.g. a landing site) where the flight path is generated while taking into consideration flight constraints existing in the area and avoiding violation of the flight constraints. The flight path is then used for autonomous generation of flight instructions for controlling the aircraft and leading the aircraft to the desired destination.

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