Method of constructing a fixed-wing aircraft

Patent metadata

Field	Value
Publication number	US-9688382-B2
Application number	US-83331910-A
Country	US
Kind code	B2
Filing date	Jul 9, 2010
Priority date	Jul 16, 2009
Publication date	Jun 27, 2017
Grant date	Jun 27, 2017

Abstract

The following steps are performed in the method of constructing an aircraft: taking a subassembly comprising two wings that are rigidly fastened together, and fitting it to a fuselage wall; and fastening the subassembly to the wall by means of fastener elements that are distinct from the subassembly and that present main axes that are vertical.

First claim

The invention claimed is:

1. A method of constructing an aircraft comprising:
taking a subassembly comprising two wings and a central wing box,
connecting each wing to the central wing box with at least one splice plate,
fastening each wing and the box to the splice plate by means of shear elements,
fitting the subassembly to a wall of a fuselage, wherein the fuselage includes a recessed portion, and
after the connecting step, fastening the subassembly to the fuselage wall by means of fastener members that are distinct from the subassembly and that present main axes that are vertical in such a manner that the fastener members pass through the splice plate or at least one of the splice plates,
wherein the aircraft is not a scale model or a mock-up, and the subassembly is mounted within the recessed portion of the fuselage.

2. A method according to claim 1 , wherein the subassembly comprises a side wall connecting together top and bottom panels of the wing, and the subassembly is fastened to the fuselage wall in such a manner that the fastener members pass through the side wall.

3. A method according to claim 1 , wherein the wall carries at least one fitting prior to the subassembly being fitted thereto, and the subassembly is fastened to the wall in such a manner that the fastener members pass through the fitting or at least one of the fittings.

4. A method according to claim 1 , wherein the subassembly includes at least one main wing panel in the form of a single part common to both wings.

5. A method according to claim 1 , wherein the fuselage wall is made of a composite material.

6. An aircraft, comprising:
a subassembly comprising two wings and a central wing box, wherein each wing is connected to the central wing box with at least one splice plate such that each wing and the central wing box are rigidly fastened to the splice plate by means of shear elements, and
a fuselage wall fastened to the subassembly by means of fastener members that are distinct from the subassembly, and that present main axes that are vertical,
wherein the aircraft is not a scale model or a mock-up, and the subassembly is mounted within a recessed portion of the fuselage.

7. An aircraft according to claim 6 , wherein the fastener members comprise a fastener bolt and a nut, the wall carrying at least one fitting presenting a vertical orifice occupied by the fastener bolt and a transverse orifice occupied by the nut.

8. A subassembly for an aircraft having a fuselage, wherein the subassembly comprises two wings rigidly fastened together independently of any wall of the fuselage, the subassembly including housings opening out into a top portion of the subassembly at a proximal end of each wing and extending vertically, wherein the housing are integrally distant from a wing trailing edge and wherein, after the subassembly is built, the subassembly is fastened to a wall by fastener members and is mounted within a recessed portion of the fuselage, and wherein the subassembly is not a scale model or mock-up.

9. An aircraft fuselage portion, including a fuselage wall, and at least one fitting carried by the wall at a bottom edge of the wall and presenting a housing opening out in the bottom portion of the fitting and extending vertically, the wall carrying two fittings extending on opposing faces of a same wall of the fuselage portion and the fittings are fastened to each other in a zone of mutual contact of the fittings with each other, wherein the aircraft fuselage portion is not a scale model or a mock-up.

10. A method of constructing an aircraft, the method comprising the following steps:
taking a subassembly comprising two wings that are rigidly fastened together, and fitting it to a fuselage wall; and
fastening the subassembly to the wall by means of fastener members that are distinct from the subassembly and that present main axes that are vertical,
wherein the subassembly includes housings opening out into a top portion of the subassembly at a proximal end of each wing and extending vertically,
wherein the aircraft is not a scale model or mock-up.

11. The method according to claim 10 , wherein the housings are integrally distant from a wing trailing edge.

12. The method according to claim 1 , wherein the subassembly is fastened directly to the wall by means of the fastener members.

13. The aircraft according to claim 6 , wherein the subassembly is fastened directly to the wall by means of the fastener members.

14. The method according to claim 10 , wherein the subassembly is fastened directly to the wall by means of the fastener members.

Assignees

• Delahaye Romain
• Gallant Guillaume
• Airbus Operations Sas

Inventors

• Delahaye Romain
• Gallant Guillaume

Classifications

• B64C2001/0072

  from composite materials · CPC title

• B64C1/26 Primary

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

• Y10T29/49947

  by applying separate fastener · CPC title

• Y02T50/433

  Cross-Sectional Technologies · mapped topic

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title