Wing tip device attachment apparatus and method

Patent metadata

Field	Value
Publication number	US-10745113-B2
Application number	US-201916369222-A
Country	US
Kind code	B2
Filing date	Mar 29, 2019
Priority date	Oct 28, 2010
Publication date	Aug 18, 2020
Grant date	Aug 18, 2020

Abstract

A method of assembling a wing tip device to a wing of a powered aircraft including: providing a wing tip, providing a wing tip device, pivotably attaching the wing tip device to the wing at a first position, pivoting the wing tip device about the first position, and attaching the wing tip device to the wing at a second position spaced from the first position.

First claim

The invention is:

1. A method of assembling a wing tip device to a wing of a powered aircraft comprising the steps of:
providing a wing tip,
providing a wing tip device,
attaching the wing tip device to the wing tip at a first position on the wing tip, wherein the attachment at the first position includes a first joint;
pivoting the wing tip device about the first joint, and
after the pivoting step, attaching the wing tip device to the wing tip at a second position on the wing tip, wherein the second position is spaced from the first position in a spanwise direction of the wing.

2. The method of claim 1 , in which the first position is closer to the wing tip device than the second position, and the second position is inboard in the spanwise direction of an end of the wing tip.

3. The method of claim 1 , in which the wing tip device comprises a first beam extending from the wing tip device and into the wing tip, wherein the first beam is attached to the wing tip at both the first and second positions, and in which an outer surface of the first beam forms part of an outer aerodynamic skin of the wing tip.

4. A method of assembling a wing tip device to a wing of a powered aircraft in which the wing tip device comprises:
a first beam extending from the wing tip device, the first beam includes a first attachment formation forming a portion of the first joint;
a second beam extending from the wing tip device and spaced in a chordwise direction from the first beam;
the method comprises:
attaching the wing tip device to the wing tip at a first position on the wing tip, wherein the attachment at the first position includes a first joint;
attaching the second beam to the wing tip at a third position on the wing tip, wherein the attachment at the third position forms a third joint,
pivoting the wing tip device about the first and third joints, and
after the pivoting step, attaching the wing tip device to the wing tip at a second position on the wing tip spaced from the first position.

5. The method of claim 4 wherein, during the pivoting step, the wing tip device is pivoted above an axis of rotation of the wing tip device which extends through the first and second joints.

6. The method of claim 4 wherein the first beam includes a second attachment formation and the step of attaching the wing tip device to the wing tip at the second position comprises attaching the wing tip device to the wing tip using the second attachment formation.

7. The method of claim 1 , wherein the wing tip is a region of the wing including a rib and a portion of at least one spar.

8. A method of mounting a wing tip device to a wing of a powered aircraft, wherein the wing tip device includes a main beam that extends in a span-wise direction from a root of the wing tip device;
aligning a first attachment point on the main beam with a first corresponding attachment point on the wing;
forming a first joint between the first attachment point of the main beam and the first corresponding attachment point on the wing;
pivoting the wing tip device about the first joint to align a second attachment point on the main beam with a second corresponding attachment point on the wing; and
fastening the second attachment point of the main beam to the second corresponding attachment point on the wing, wherein the second attachment point is spaced from the first attachment point in a spanwise direction of the wing.

9. A method of mounting a wing tip device to a wing of a powered aircraft, wherein the wing tip device further includes a spar which extends in the span-wise direction from the root of the wing tip device, and the main beam and spar are separated in a chordwise direction, and the method comprises:
aligning a first attachment point on the main beam with a first corresponding attachment point on the wing;
forming a first joint between the first attachment point of the main beam and the first corresponding attachment point on the wing;
pivoting the wing tip device about the first joint to align a second attachment point on the main beam with a second corresponding attachment point on the wing;
fastening the second attachment point of the main beam to the second corresponding attachment point on the wing;
aligning a third attachment point on the spar with a third corresponding attachment point on the wing, and
forming a third joint between the third attachment point of the spar and the third corresponding attachment point on the wing,
wherein the step of pivoting the wing tip device includes pivoting the wing tip device about an axis of rotation extending through the first and third attachment points.

10. A method of mounting a wing tip device to a wing of a powered aircraft, wherein the wing is a fixed wing of the powered aircraft and the wing tip device includes a main beam that extends in a span-wise direction from a root of the wing tip device;
aligning a first attachment point on the main beam with a first corresponding attachment point on the wing;
forming a first joint between the first attachment point of the main beam and the first corresponding attachment point on the wing;
pivoting the wing tip device about the first joint to align a second attachment point on the main beam with a second corresponding attachment point on the wing; and
fastening the second attachment point of the main beam to the second corresponding attachment point on the wing.

11. The method of claim 10 , wherein the first corresponding attachment point is proximate an end of the fixed wing, and the second corresponding attachment point is inboard of the first attachment point.

Assignees

• Airbus Operations Ltd

Inventors

• Chaussee Julien
• Paumes Camille
• Wijker Norman
• Alexander Stuart

Classifications

• B64C3/56

  Folding or collapsing to reduce overall dimensions of aircraft · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64C23/072 Primary

  the wing tip airfoil devices being moveable in their entirety · CPC title

• Y10T29/49826

  Assembling or joining · CPC title

• Y02T50/164

  Cross-Sectional Technologies · mapped topic