Integrated ribs for central wing box

Patent metadata

Field	Value
Publication number	US-10399663-B2
Application number	US-201615255639-A
Country	US
Kind code	B2
Filing date	Sep 2, 2016
Priority date	Sep 4, 2015
Publication date	Sep 3, 2019
Grant date	Sep 3, 2019

Abstract

A central wing box for an aircraft, including a top panel, a bottom panel, a front spar, a rear spar, and at least one secondary rib. A secondary rib includes two stiffeners, a first stiffener extending adjacent to the top panel and to one of the front spar and the rear spar, and a second stiffener extending adjacent to the bottom panel and to the other of the front spar and the rear spar. A reduced number of components can be employed, thereby simplifying the construction of the central wing box of an aircraft, particularly the installation of the secondary ribs.

First claim

The invention claimed is:

1. A central wing box for an aircraft, the central wing box comprising:
a top panel;
a bottom panel;
a front spar;
a rear spar; and
at least one internal rib, each internal rib comprising first and second stiffeners arranged inside a volume delimited by the top panel, the bottom panel, the front spar, and the rear spar;
wherein the first stiffener extends, adjacent to the top panel and to one of the front spar or the rear spar, over more than three quarters of an extent of respective profiles of the top panel and of the front or rear spar inside the central wing box; and
wherein the second stiffener extends, adjacent to the bottom panel and to whichever of the front spar or the rear spar the first stiffener is not adjacent, over more than three quarters of the extent of the respective profiles of the bottom panel and of the front or rear spar inside the central wing box.

2. The central wing box according to claim 1 , wherein the profile of the top panel and/or the profile of the bottom panel comprises an entire length of the central wing box.

3. The central wing box according to claim 1 , wherein at least one stiffener comprises:
a first leg extending adjacent to the top or bottom panel and having a first end and a second end;
a second leg extending adjacent to the front or rear spar and having a first end and a second end, the first end of the first leg and the first end of the second leg being joined together; and
a reinforcing element extending from the first leg to the second leg.

4. The central wing box according to claim 3 , wherein the reinforcing element extends from the second end of the second leg to a support region of the first leg, the support region being situated a distance from the first and second ends of the first leg.

5. The central wing box according to claim 3 , wherein the reinforcing element extends from a support region of the second leg to a support region of the first leg, the support region of the first leg being situated a distance from the first and second ends of the first leg and the support region of the second leg being situated a distance from the first and second ends of the second leg.

6. The central wing box according to claim 3 , wherein the at least one stiffener comprises a through-opening extending between the reinforcing element, the first leg, and the second leg associated with said at least one stiffener.

7. The central wing box according to claim 3 , wherein a region of the at least one stiffener, which is situated between the reinforcing element, the first leg, and the second leg, is solid and comprises a mechanical strength that is lower than a mechanical strength of the reinforcing element.

8. The wing box according to claim 3 , wherein the second ends of the first and second legs of each stiffener of a same internal rib are superposed in pairs.

9. The central wing box according to claim 3 , wherein second ends of the first and second legs of each stiffener of a same internal rib are joined together in pairs.

10. The central wing box according to claim 3 , wherein the at least one stiffener comprises a series of cavities that are distributed along the first leg and adapted to accommodate stiffeners of whichever of the bottom or top panel to which the first leg is adjacent.

11. A method of installing an internal rib of a central wing box comprising a top panel, a bottom panel, a front spar, a rear spar, and at least one internal rib, each internal rib comprising first and second stiffeners arranged inside a volume delimited by the top panel, the bottom panel, the front spar, and the rear spar, the method comprising:
installing the first stiffener inside the central wing box at a position adjacent to the top panel and to one of the front spar and the rear spar so that the first stiffener extends over more than three quarters of an extent of respective profiles of the top panel and of the front spar or rear spar; and
installing the second stiffener inside the central wing box at a position adjacent to the bottom panel and to whichever of the front spar and the rear spar the first stiffener is not adjacent so that the first stiffener extends over more than three quarters of an extent of respective profiles of the bottom panel and of whichever of the front spar or rear spar the first stiffener is not adjacent.

12. The method according to claim 11 , wherein the profile of the top panel and/or the profile of the bottom panel comprises an entire length of the central wing box.

13. The method according to claim 11 , wherein at least one stiffener comprises:
a first leg extending adjacent to the top or bottom panel and having a first end and a second end;
a second leg extending adjacent to the front or rear spar and having a first end and a second end, the first end of the first leg and the first end of the second leg being joined together; and
a reinforcing element extending from the first leg to the second leg.

14. The method according to claim 13 , wherein the reinforcing element extends from the second end of the second leg to a support region of the first leg, the support region being situated a distance from the first and second ends of the first leg.

15. The method according to claim 13 , wherein the reinforcing element extends from a support region of the second leg to a support region of the first leg, the support region of the first leg being situated a distance from the first and second ends of the first leg and the support region of the second leg being situated a distance from the first and second ends of the second leg.

16. The method according to claim 13 , wherein the at least one stiffener comprises a through-opening extending between the reinforcing element, the first leg, and the second leg associated with said at least one stiffener.

17. The method according to claim 13 , wherein a region of the at least one stiffener, which is situated between the reinforcing element, the first leg, and the second leg, is solid and comprises a mechanical strength that is lower than a mechanical strength of the reinforcing element.

18. The method according to claim 13 , wherein the second ends of the first and second legs of each stiffener of a same internal rib are superposed in pairs.

19. The method according to claim 13 , wherein second ends of the first and second legs of each stiffener of a same internal rib are joined together in pairs.

20. The method according to claim 13 , wherein the at least one stiffener comprises a series of cavities that are distributed along the first leg and adapted to accommodate stiffeners of whichever of the bottom or top panel to which the first leg is adjacent.

Assignees

• Airbus Operations Sas

Inventors

• Soula Denis
• Plet Matthieu
• Maqueda Lahoz Javier

Classifications

• B64C3/185

  Spars · CPC title

• B64C3/187 Primary

  Ribs · CPC title

• B64C3/00 Primary

  Wings (ornithopter wings B64C33/02) · CPC title

• B64C3/22

  Geodetic or other open-frame structures · CPC title

• B64C1/26

  Attaching the wing or tail units or stabilising surfaces · CPC title