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.