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公开(公告)号：US11970275B2
公开(公告)日：2024-04-30
申请号：US17583467
申请日：2022-01-25
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Danny Abramov , Shay Hemo
CPC classification number: B64D27/24 , B64C11/46 , B64C29/0025 , B64U50/13 , B64C2009/005 , B64C9/38
Abstract: An air vehicle is provided including: a main lift generating wing arrangement having a port wing and a starboard wing, empennage and main propulsion system. The air vehicle further includes a distributed electrical propulsion (DEP) system having secondary electrical propulsion units coupled to each one of the port wing and the starboard wing. The main propulsion system is configured for providing sufficient thrust such as to enable powered aerodynamic flight of the air vehicle including at least: powered aerodynamic take off absent operation of the DEP system; and powered aerodynamic landing absent operation of the DEP system. The DEP system is configured for selectively providing at least augmented lift to the main lift generating wing arrangement in at least landing. A method for landing an air vehicle on a moving platform under separated wake conditions is also provided.
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公开(公告)号：US20160347451A1
公开(公告)日：2016-12-01
申请号：US15113368
申请日：2015-01-27
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Michael Shepshelovich , Danny Abramov , Yonatan Klein
CPC classification number: B64C39/024 , B64C3/14 , B64C13/16 , B64C15/12 , B64C29/00 , B64C2201/084 , B64C2201/104 , B64D43/02 , Y02T50/12
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.
Abstract translation: 提供了用于操作具有固定翼的机动车辆的方法。 这样的方法包括提供与固定翼相关的迎角与雷诺数相关的操作图的步骤，包括在固定翼上分离的流动的条件以及固定翼上附着流的条件。 这种方法还包括使用操作图来进行引导的步骤，使得空中飞行器至少在对应于操作图的低雷诺数范围内操作，以避免或最小化导致飞行器在条件下操作的风险 分离流过固定翼。
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公开(公告)号：US12097948B2
公开(公告)日：2024-09-24
申请号：US18596947
申请日：2024-03-06
Applicant: Israel Aerospace Industries Ltd.
Inventor： Danny Abramov , Shai Alexandroni , Ben Keshales
Abstract: A propulsion system, including a rotor arrangement rotatably mounted with respect to a nacelle about a rotor axis. The rotor arrangement includes rotor blades, each being pivotably mounted to a hub element about a respective blade pivot axis, the rotor blades being deployable between an undeployed configuration and a deployed configuration. The nacelle includes a nacelle body having a nacelle outer surface including facet elements and transition elements, each facet element extending aft from the hub element, each adjacent pair of facet elements being circumferentially spaced from one another by a corresponding transition element, each facet element having a first curvature with respect to the rotor axis, each transition element having a second curvature with respect to the rotor axis. The first curvature is different from the second curvature. In the undeployed configuration, each rotor blade is in overlying and fully external relationship with respect to a corresponding facet element.
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公开(公告)号：US20220355932A1
公开(公告)日：2022-11-10
申请号：US17623492
申请日：2020-07-06
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Danny Abramov , Artem Korobkov , Ron Bublitsky
Abstract: There is provided a composite air vehicle system including: a first air vehicle capable of independent aerodynamic flight; a second air vehicle capable of independent aerodynamic flight; and at least one connector element configured for reversibly interconnecting the first air vehicle and the second air vehicle in tandem arrangement to provide a composite air vehicle capable of aerodynamic flight. The composite air vehicle system is configured for enabling at least in-flight separation of composite air vehicle into the first air vehicle and second air vehicle, and for enabling each one of the first air vehicle and said second air vehicle to operate independently of one another.
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公开(公告)号：US20160342160A1
公开(公告)日：2016-11-24
申请号：US15108711
申请日：2014-12-09
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Michael Shepshelovich , Danny Abramov
Abstract: Methods are provided for operating an air vehicle, the air vehicle including fixed wings configured to provide mild stall characteristics including a post-stall regime, and a propulsion system capable of generating a controllable thrust, the thrust being variable at least between an idle thrust and a maximum thrust. During a landing maneuver, the air vehicle is caused to attain an angle of attack corresponding to said post-stall regime, and during the landing maneuver, there is concurrently generated a thrust level of said thrust greater than said idle thrust to provide a thrust vector having a thrust lift force component at landing. Corresponding control systems are also provided, and air vehicles including such control systems are also provided.
Abstract translation: 提供了用于操作空中飞行器的方法，所述空中飞行器包括被配置为提供包括后停止状态的温和失速特性的固定翼和能够产生可控推力的推进系统，所述推力至少在空转推力和 最大推力。 在着陆操作期间，使空中飞行器达到对应于所述后失速状态的攻角，并且在着陆操作期间，同时产生所述推力的推力水平大于所述空转推力以提供推力矢量 在着陆时具有推力提升力分量。 还提供了相应的控制系统，还提供了包括这种控制系统的机动车辆。
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Patent Agency Ranking
公开(公告)号：US20230211902A1
公开(公告)日：2023-07-06
申请号：US18000960
申请日：2021-06-24
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Danny Abramov , Yoav Heichal
Abstract: 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.
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公开(公告)号：US10423168B2
公开(公告)日：2019-09-24
申请号：US15108711
申请日：2014-12-09
Applicant: Israel Aerospace Industries Ltd.
Inventor： Michael Shepshelovich , Danny Abramov
Abstract: Methods are provided for operating an air vehicle, the air vehicle including fixed wings configured to provide mild stall characteristics including a post-stall regime, and a propulsion system capable of generating a controllable thrust, the thrust being variable at least between an idle thrust and a maximum thrust. During a landing maneuver, the air vehicle is caused to attain an angle of attack corresponding to said post-stall regime, and during the landing maneuver, there is concurrently generated a thrust level of said thrust greater than said idle thrust to provide a thrust vector having a thrust lift force component at landing. Corresponding control systems are also provided, and air vehicles including such control systems are also provided.
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公开(公告)号：US10279907B2
公开(公告)日：2019-05-07
申请号：US15113368
申请日：2015-01-27
Applicant: Israel Aerospace Industries Ltd.
Inventor： Michael Shepshelovich , Danny Abramov , Yonatan Klein
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.
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公开(公告)号：US11912435B2
公开(公告)日：2024-02-27
申请号：US17623492
申请日：2020-07-06
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Danny Abramov , Artem Korobkov , Ron Bublitsky
CPC classification number: B64D5/00 , B64C37/02 , B64C39/024 , B64C39/08 , B64C39/12 , B64D3/00 , B64C2211/00 , B64U10/25 , B64U30/10
Abstract: There is provided a composite air vehicle system including: a first air vehicle capable of independent aerodynamic flight; a second air vehicle capable of independent aerodynamic flight; and at least one connector element configured for reversibly interconnecting the first air vehicle and the second air vehicle in tandem arrangement to provide a composite air vehicle capable of aerodynamic flight. The composite air vehicle system is configured for enabling at least in-flight separation of composite air vehicle into the first air vehicle and second air vehicle, and for enabling each one of the first air vehicle and said second air vehicle to operate independently of one another.
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公开(公告)号：US20230211869A1
公开(公告)日：2023-07-06
申请号：US18000840
申请日：2021-06-08
Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.
Inventor： Danny Abramov , Yonatan Klein
Abstract: A wing system is provided for an air vehicle, the wing system having a stowed configuration, a pre-deployed configuration, and a deployed configuration. The wing system includes two wings, each wing having aerofoil profiles and being pivotably deployable about a respective pivot axis between the pre-deployed configuration and the deployed configuration. In the stowed configuration the two wings are in first general superposed spatial relationship with respect to one another and are capable of being accommodated within an envelope having an envelope cross-sectional profile and a corresponding envelope cross-sectional area. In the pre-deployed configuration, the two wings are in second general superposed spatial relationship with respect to one another and capable of deploying to the deployed configuration. In the deployed configuration the wings are each capable of generating aerodynamic lift in an airstream. Each aerofoil profile of each wing is a slotted aerofoil having a primary element, a secondary element and a chord, the secondary element being pivotable with respect to the primary element and spaced therefrom by a gap. Each aerofoil profile has a respective maximum thickness, and a respective maximum absolute thickness. In the stowed configuration, the respective second element of eachaerofoil of one wing is set at a different flap angle as compared with the respective second element of each aerofoil of the other wing.
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