Attachment concept for a fairing on an airfoil body such as a flap or a wing of an aircraft

Patent metadata

Field	Value
Publication number	US-12043397-B2
Application number	US-202217841145-A
Country	US
Kind code	B2
Filing date	Jun 15, 2022
Priority date	Jun 18, 2021
Publication date	Jul 23, 2024
Grant date	Jul 23, 2024

Abstract

An arrangement comprising an airfoil body, a junction mechanism for attaching the airfoil body to a support element of an aircraft, and a fairing for aerodynamically covering the junction mechanism. The fairing has a cover element covering a trailing end portion of the fairing. The cover element is attached to the trailing edge of the airfoil body by a form fit connection.

First claim

The invention claimed is:

1. An arrangement comprising:
an airfoil body, and
a fairing aerodynamically covering at least a part of a junction mechanism connecting the airfoil body to a support element of an aircraft,
the fairing having a cover element covering a trailing end portion of the fairing,
wherein the cover element is attached to a trailing edge of the airfoil body by a form fit connection, and
wherein the junction mechanism is located forward of the trailing edge of the airfoil body and allows relative movement between the airfoil body and the support element.

2. The arrangement according to claim 1 ,
wherein the form fit connection comprises a male-female interlock joint,
wherein one of a leading end of the cover element and the trailing edge of the airfoil body has a female connecting part and the other of the leading end of the cover element and the trailing edge of the airfoil body has a male connecting part inserted into the female connecting part.

3. The arrangement according to claim 1 , wherein the form fit connection is a tongue and groove connection wherein one of a leading end of the cover element and the trailing edge of the airfoil body has a groove and the other of the leading end of the cover element and the trailing edge of the airfoil body has a tongue inserted into the groove.

4. The arrangement according to claim 3 , wherein the tongue and groove connection extends over at least a major part of a width of the fairing measured in a spanwise direction of the airfoil body.

5. The arrangement according to claim 3 , wherein the tongue is thicker than the groove so that the tongue is clampable within the groove.

6. The arrangement according to claim 3 , wherein the leading end of the cover element has the groove, the tongue is formed by the trailing edge of the airfoil body, and an aerodynamic sealing seals a transition area between the airfoil body and the cover element.

7. The arrangement according to claim 1 , wherein the form fit connection is configured to bear vertical loads and wherein an additional fixation device bears loads in at least one of spanwise and chordwise directions.

8. The arrangement according to claim 7 , wherein the additional fixation device comprises at least one of a fastener, a shear pin, a snap-fit connection, a projection on one of the cover element and the airfoil body inserted in a recess on the other of the cover element and the airfoil body, and a strip on one of the cover element and the airfoil body inserted into a groove-like recess of the other of the cover element and the airfoil body.

9. The arrangement according to claim 1 , wherein a front portion of the fairing is additionally attached to a bracket fixed to a structural element of the airfoil body.

10. The arrangement according to claim 1 , wherein the airfoil body is a flap of a high-lift system for an aircraft.

11. The arrangement according to claim 1 , further comprising the junction mechanism for connecting the airfoil body to a support element of an aircraft.

12. An aircraft, comprising an arrangement according to claim 1 .

13. A method for installing a fairing of the arrangement of claim 1 to an airfoil body, comprising:
moving the fairing and the airfoil body relative to each other to insert one of a trailing edge of the airfoil body and a leading end of a cover element into the other of the trailing edge of the airfoil body and the leading end of the cover element, and
deforming at least one of the trailing edge of the airfoil body and the leading end of the cover element by the insertion so that a reaction force causes the trailing edge and the leading end to be clamped together.

14. The method according to claim 13 , comprising displacing the airfoil body and the fairing in a linear movement relative to each other in order to engage the form fit connection to provide a rear attachment.

15. The method according to claim 13 , comprising rotating the airfoil body and the fairing relative to each other in order to engage the form fit connection to provide a rear attachment.

16. An arrangement comprising:
an aircraft support element;
one of an elevator, a flap, a slat, an elevator, a rudder, or an aileron
a moving mechanism joining the one of the elevator, the flap, the slat, the elevator, the rudder, or the aileron to the aircraft support element, the moving mechanism allowing relative movement between the aircraft support element and the one of the elevator, the flap, the slat, the elevator, the rudder, or the aileron;
a fairing aerodynamically covering at least a part of the moving mechanism, the fairing having a cover covering a trailing end portion of the fairing,
wherein the cover element is attached to a trailing edge of the one of the elevator, the flap, the slat, the elevator, the rudder, or the aileron by a form fit connection.

Assignees

• Airbus Operations Gmbh

Inventors

• Daandels Dort
• Ewald Jörn

Classifications

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C3/28

  Leading or trailing edges attached to primary structures, e.g. forming fixed slots · CPC title

• B64C3/50

  by leading or trailing edge flaps · CPC title

• B64D29/06 Primary

  Attaching of nacelles, fairings or cowlings · CPC title

• B64C7/00 Primary

  Structures or fairings not otherwise provided for · CPC title