Aircraft wing with spoiler

Patent metadata

Field	Value
Publication number	US-2017190413-A1
Application number	US-201615384509-A
Country	US
Kind code	A1
Filing date	Dec 20, 2016
Priority date	Dec 30, 2015
Publication date	Jul 6, 2017
Grant date	—

Abstract

An aircraft wing has a spoiler movable from a reference position with a deflection angle α ref to a given target deflection angle α target by an actuator powered mechanism. An upstream edge of the spoiler is interconnected with the aircraft wing exclusively via a strip element made of a resiliently flexible material and via the actuator powered mechanism. A downstream edge of the strip element extends along the whole or at least along a major part of the upstream edge of the spoiler. The actuator powered mechanism is constructed and arranged such that, while moving the spoiler, the strip element is bent with a constant strain along the strip element. A cross-section of the strip element for all deflection angles α assumes the form of a ring segment with a radius R(α) at least within a given margin of failure, with α, α target , α ref ε[−α 1 ; α 2 ].

First claim

1 . An aircraft wing with a spoiler, the spoiler being movable from a reference position with a deflection angle α ref to a given target deflection angle α target by an actuator powered mechanism wherein
the spoiler is interconnected with the aircraft wing exclusively via a strip element and via the actuator powered mechanism, wherein
an upstream edge of the spoiler is interconnected with the aircraft wing exclusively via the strip element made of a resiliently flexible material, wherein a downstream edge of the strip element extends along the whole upstream edge of the spoiler or at least along a major part of the upstream edge of the spoiler and wherein a whole upstream edge of the strip element is connected to an upper surface of the aircraft wing, and
the actuator powered mechanism is constructed and arranged such that while moving the spoiler from the reference angle α ref to the given target deflection angle α target , the strip element is bent with a constant strain along the strip element, wherein a cross-section of the strip element for all deflection angles α assumes the form of a ring segment with a radius R(α) at least within a given margin of failure, with α, α target , α ref ε[−α 1 ; α 2 ].

2 . The aircraft wing of claim 1 , wherein a passage from the upper surface of the aircraft wing via the upper surface of the strip element to the upper surface of the spoiler is a smooth surface.

3 . The aircraft wing of claim 1 , wherein the spoiler is a high lift spoiler.

4 . The aircraft wing of claim 1 , wherein the target deflection angle α target is selected from the interval: αε[−30°; 60°].

5 . The aircraft wing of claim 1 , wherein the given margin of failure indicating a deviation of the form of the actual cross-section of the strip element from the respective ring segment with a radius R(α) is less than 15%.

6 . The aircraft wing of claim 1 ,
wherein the actuator powered mechanism comprises a guidance kinematic, a guidance lever and an actuator, wherein: the guidance kinematic is fixed to a contact C1 on an inner structure of the airfoil, a first end of the guidance lever is rigidly connected to a contact C2 on a lower side of the spoiler, two connecting elements separated by a distance D are connected to a second end of the guidance lever, the connecting elements are movably coupled to the guidance kinematic, wherein the connecting elements exclusively allow a movement of the first end guidance lever along the guidance kinematic, the actuator is fixed to an inner structure of the aircraft wing and further is connected to the guidance lever for moving the guidance lever along the guidance kinematic, the movement being dependant on a given target deflection angle α target , and wherein any deflection angle αε[−α 1 ; α 2 ] corresponds to a distinct position of the guidance lever along the guidance kinematic, and wherein the guidance kinematic has a 3D-form such that the spoiler for all deflection angles α is articulated by the guidance lever such that the cross-section of the flexible strip element for all deflection angles α assumes the form of said ring segment with a radius R(α) at least within a given margin of failure, with α, α target , α ref ε[−α 1 ; α 2 ].

7 . The aircraft wing of claim 6 , wherein the connecting elements comprise rollers.

8 . The aircraft wing of claim 1 , wherein the actuator powered mechanism is constructed and arranged such that the majority of an air load on the spoiler is transferred via the actuator powered mechanism to the airfoil, wherein a minimum of the air load is transferred to an actuator of the actuator powered mechanism.

9 . The aircraft wing of claim 8 , wherein the actuator powered mechanism is constructed such that 85% of the air load on the spoiler is transferred via the actuator powered mechanism to the aircraft wing and that less than 15%, are transferred to the actuator.

10 . The aircraft wing of claim 6 , wherein the guidance lever is variable in its length L depending on deflection angle α: L=L(α).

11 . The aircraft wing of claim 1 , wherein the actuator powered mechanism is integrated in the aircraft wing.

12 . The aircraft wing of claim 1 , wherein a virtual center position CP(α) of the ring segment with the radius R(α) varies with α.

13 . The aircraft wing of claim 1 , wherein the spoiler comprises at least the following segments:
an upstream segment SEG 1 with a stiffness S 1 , a downstream segment SEG 2 with a stiffness S 2 , a connecting segment SEG 3 with a stiffness S 3 , the connecting segment SEG 3 is connecting a downstream edge of SEG 1 with an upstream edge of SEG 2 , the strip element connecting an upstream edge of SEG 1 to the upper surface of the aircraft wing, wherein at least the connecting segment SEG 3 possesses a mechanical pretension, which would, if no forces are acting on the spoiler, result in a given convex shape of the upper surface of the spoiler, with S 3 <S 1 , S 2 .

14 . The aircraft wing ( 100 ) of claim 1 , wherein a virtual center position CP(α) of the ring segment with the radius R(α) varies with α.

15 . An aircraft or spaceship with an aircraft wing, wherein the aircraft wing comprises a spoiler, the spoiler being movable from a reference position with a deflection angle α ref to a given target deflection angle α target by an actuator powered mechanism wherein
the spoiler is interconnected with the aircraft wing exclusively via a strip element and via the actuator powered mechanism, wherein
an upstream edge of the spoiler is interconnected with the aircraft wing exclusively via the strip element made of a resiliently flexible material, wherein a downstream edge of the strip element extends along the whole upstream edge of the spoiler or at least along a major part of the upstream edge of the spoiler and wherein a whole upstream edge of the strip element is connected to an upper surface of the aircraft wing, and the actuator powered mechanism is constructed and arranged such that while moving the spoiler from the reference angle α ref to the given target deflection angle α target , the strip element is bent with a constant strain along the strip element, wherein a cross-section of the strip element for all deflection angles α assumes the form of a ring segment with a radius R(α) at least within a given margin of failure, with α, α target , α ref ε[−α 1 ; α 2 ].

Assignees

• Airbus Defence & Space Gmbh
• Airbus Operations Gmbh

Inventors

• Hansen Heinz
• Kirn Johannes
• Machunze Wolfgang
• Metzner Christian
• Weber Markus J

Classifications

• B64C13/341

  having duplication or stand-by provisions · CPC title

• B64C3/58 Primary

  provided with fences or spoilers (adjustable for control purposes B64C9/00) · CPC title

• B64C9/323

  associated with wings · CPC title

• B64C9/14 Primary

  forming slots · CPC title

• B64C13/28

  mechanical · CPC title