公开(公告)号：WO2014199371A8

公开(公告)日：2014-12-18

申请号：PCT/IL2014/050513

申请日：2014-06-08

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： SHEPSHELOVICH, Michael ,  ABRAMOV, Danny

IPC: B64C3/14 ,  B64C9/32

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.

公开(公告)号：WO2016055990A1

公开(公告)日：2016-04-14

申请号：PCT/IL2014/051077

申请日：2014-12-09

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： SHEPSHELOVICH, Michael ,  ABRAMOV, Danny

IPC: B64C3/14 ,  B64C3/50

CPC classification number: G05D1/0808 ,  B64C3/14 ,  B64C3/50 ,  B64C9/20 ,  B64C9/323 ,  B64C39/024 ,  B64C2201/187 ,  B64D31/06 ,  B64D45/04 ,  Y02T50/14 ,  Y02T50/32

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，该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。

公开(公告)号：WO2010032241A1

公开(公告)日：2010-03-25

申请号：PCT/IL2009/000904

申请日：2009-09-16

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD. ,  SHEPSHELOVICH, Michael ,  NAGEL, Alex ,  ABRAMOV, Danny

Inventor： SHEPSHELOVICH, Michael ,  NAGEL, Alex ,  ABRAMOV, Danny

IPC: B64C3/44

CPC classification number: B64C3/48 ,  B64C3/14 ,  B64C3/44 ,  B64C2003/142 ,  B64C2003/148 ,  Y02T50/12 ,  Y02T50/14

Abstract: Aerofoil accessories are provided (10, 510), configured for selective attachment to a wing element (32), the wing element (32) having an outer facing aerofoil surface and being based on at least one datum aerofoil section. Each accessory (10, 510) provides a modified geometric profile to a datum profile of the at least one aerofoil section when attached to the wing element. The accessories (10, 510) 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.

Abstract translation: 提供的翼型配件（10,510）被配置为选择性地附接到翼元件（32），翼元件（32）具有外表面的翼面，并且基于至少一个基准翼型部分。 当附接到翼元件时，每个附件（10,510）向至少一个机翼部分的基准轮廓提供改进的几何轮廓。 至少每当所述机翼元件空气传播时，附件（10,510）都被配置为相对于至少一个基准翼型部分具有基本上固定的几何轮廓，相应的附件附接到机翼元件。 改进的几何轮廓是为了使所述翼元件具有附接到其上的附件，其具有相对于没有附件的机翼元件提供的基准性能的期望性能变化。 还提供了一个套件，用于在非设计条件下增强机翼元件的性能。 还提供了用于在不利条件下增强机翼元件的性能的方法。

公开(公告)号：WO2021005595A1

公开(公告)日：2021-01-14

申请号：PCT/IL2020/050755

申请日：2020-07-06

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： ABRAMOV, Danny ,  KOROBKOV, Artem ,  BUBLITSKY, Ron

IPC: B64C37/02 ,  B64D5/00 ,  B64C39/08 ,  B64C39/12 ,  B64D3/00

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.

公开(公告)号：WO2010032240A2

公开(公告)日：2010-03-25

申请号：PCT/IL2009/000903

申请日：2009-09-16

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD. ,  SHEPSHELOVICH, Michael ,  ABRAMOV, Danny

Inventor： SHEPSHELOVICH, Michael ,  ABRAMOV, Danny

IPC: B64C3/44 ,  B64C3/14

CPC classification number: B64C3/48 ,  B64C3/14 ,  B64C3/44 ,  B64C2003/142 ,  B64C2003/148 ,  Y02T50/12 ,  Y02T50/14

Abstract: A two element aerofoil, and wing element based thereon, is provided, including a primary aerofoil element including a leading edge of the aerofoil and a secondary aerofoil element including a trailing edge of the aerofoil. A gap is provided between the primary aerofoil element and the secondary aerofoil element. The primary aerofoil element has at least one of a profile, orientation and location with respect to a respective at least one of a profile, orientation and location of the secondary aerofoil element that is configured for minimizing or avoiding accretion of contaminant on the secondary aerofoil element when subjected to an airflow that includes the contaminant, at least at one design set of conditions. A method for designing a two element aerofoil is also provided.

Abstract translation: 提供了一种两元件机翼和基于此的翼元件，其包括包括机翼的前缘的主要翼型元件和包括机翼后缘的次级机翼元件。 在主翼型元件和次级机翼元件之间提供间隙。 主翼面元件具有相对于次级翼型元件的轮廓，取向和位置中的相应的至少一个的轮廓，取向和位置中的至少一个，其被配置为最小化或避免在次级翼型元件上的污染物的增加 当受到包含污染物的气流时，至少在一个设计的条件下。 还提供了一种用于设计两元件机翼的方法。

公开(公告)号：WO2023037361A1

公开(公告)日：2023-03-16

申请号：PCT/IL2022/050966

申请日：2022-09-05

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： ABRAMOV, Danny ,  ALEXANDRONI, Shai ,  KESHALES, Ben

IPC: B64C27/473 ,  B64C27/46 ,  B64C11/28 ,  B64D29/02

Abstract: A propulsion system is provided, including a rotor arrangement rotatably mounted with respect to a nacelle about a rotor axis. The rotor arrangement includes a plurality of 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 a plurality of facet elements and a plurality of 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.

公开(公告)号：WO2022003672A1

公开(公告)日：2022-01-06

申请号：PCT/IL2021/050773

申请日：2021-06-24

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： ABRAMOV, Danny ,  HEICHAL, Yoav

IPC: B64C3/56 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/102 ,  B64C39/024

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.

公开(公告)号：WO2021250660A1

公开(公告)日：2021-12-16

申请号：PCT/IL2021/050684

申请日：2021-06-08

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： ABRAMOV, Danny ,  KLEIN, Yonatan

IPC: B64C3/56 ,  B64C9/16 ,  B64C2201/102 ,  B64C39/024 ,  B64C9/18

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 each aerofoil of one wing is set at a different flap angle as compared with the respective second element of each aerofoil of the other wing.

公开(公告)号：EP4161833A1

公开(公告)日：2023-04-12

申请号：EP21821894.9

申请日：2021-06-08

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： ABRAMOV, Danny ,  KLEIN, Yonatan

IPC: B64C3/56 ,  B64C9/16

公开(公告)号：EP4399150A1

公开(公告)日：2024-07-17

申请号：EP22866877.8

申请日：2022-09-05

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： ABRAMOV, Danny ,  ALEXANDRONI, Shai ,  KESHALES, Ben

IPC: B64C27/473 ,  B64C27/46 ,  B64C11/28 ,  B64D29/02

CPC classification number: B64C11/28 ,  B64D29/02 ,  B64C11/04 ,  B64C11/18 ,  B64C7/02 ,  B64D29/00