ASSEMBLY FOR AN AIRCRAFT INCLUDING A WING ELEMENT AND A SUSPENSION PYLON

• US 20100193627A1
• Filed: 09/22/2006
• Published: 08/05/2010
• Est. Priority Date: 09/26/2005
• Status: Active Grant

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus France
• Inventors: Lafont, Laurent
• Granted Patent: US 7,780,113 B1
• Time in Patent Office: Days
• US Class Current: 244/54
• CPC Class Codes: B64D 27/18 within, or attached to, wings
• CPC Class Codes: B64D 27/40 Arrangements for mounting power plants in aircraft
• CPC Class Codes: B64D 27/402 comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant

Abstract

The invention relates to an assembly for an aircraft comprising a wing element (2) and a suspension pylon (4) for an engine (10) under the wing element, the suspension pylon (4) comprising a rigid structure (6) forming a box provided with an aft closing element (28), and the wing element (2) having a forward spar (34) extending substantially parallel to a leading edge (30) of the wing element. According to the invention, the rigid structure is assembled on the wing element such that the aft closing element bears in contact with the forward spar (34).

Claims

1. An assembly for an aircraft comprising a wing element and a suspension pylon for an engine under said wing element, the suspension pylon comprising a rigid structure forming a box provided with an aft closing element, and the wing element having a forward spar extending substantially parallel to a leading edge of said wing element, wherein the rigid structure is assembled on the wing element such that the aft closing element bears in contact with said forward spar of the wing element, said rigid structure partially penetrating inside said wing element,

wherein said box includes an upper spar, a lower spar and two side panels, wherein said upper and lower spars and said two side panels are connected to each other by transverse ribs, and wherein said closing element is connected to said upper and lower spars and to said two side panels at an aft end of the box so as to at least partially close said box at said aft end of the box,

wherein the aft closing element bears in contact with said forward spar of the wing element over the entire outside surface of said aft closing element.

2-12. -12. (canceled)

13. An assembly for an aircraft comprising a wing element and a suspension pylon for an engine under said wing element, the suspension pylon comprising a rigid structure forming a box provided with an aft closing element, and the wing element having a forward spar extending substantially parallel to a leading edge of said wing element, wherein the rigid structure is assembled on the wing element such that the aft closing element bears in contact with said forward spar of the wing element, said rigid structure partially penetrating inside said wing element,

wherein said box includes an upper spar, a lower spar and two side panels, wherein said upper and lower spars and said two side panels are connected to each other by transverse ribs, and wherein said closing element is connected to said upper and lower spars and to said two side panels at an aft end of the box so as to at least partially close said box at said aft end of the box,

wherein said closing element is a plate that entirely closes said box,

wherein the aft closing element bears in contact with said forward spar of the wing element over the entire outside surface of said aft closing element.

15. An assembly according to claim 13, further comprising mounting means for fastening the aft closing element onto the wing element, said mounting means comprising two lateral shear pins and a plurality of tension bolts.

14. (canceled)

16. An assembly for an aircraft comprising a wing element and a suspension pylon for an engine under said wing element, the suspension pylon comprising a rigid structure forming a box provided with an aft closing element, and the wing element having a forward spar extending substantially parallel to a leading edge of said wing element, wherein the rigid structure is assembled on the wing element such that the aft closing element bears in contact with said forward spar of the wing element, said rigid structure partially penetrating inside said wing element,

wherein said box includes an upper spar, a lower spar and two side panels, wherein said upper and lower spars and said two side panels are connected to each other by transverse ribs, and wherein said closing element is connected to said upper and lower spars and to said two side panels at an aft end of the box so as to at least partially close said box at said aft end of the box,

wherein said rigid structure and said wing element are connected to each other solely by said closing element.

17. An assembly according to claim 16, further comprising at least one forward engine attachment connecting a forward end of said rigid structure to said engine, at least one aft engine attachment connecting an aft end of said rigid structure to said engine, and a thrust resistance device connecting said at least one forward engine attachment to said at least one aft engine attachment.

18. An assembly according to claim 17, wherein said thrust resistance device extends between said box and said engine.