Multi-Box Wing Spar and Skin

Patent metadata

Field	Value
Publication number	US-2017106968-A1
Application number	US-201615390657-A
Country	US
Kind code	A1
Filing date	Dec 26, 2016
Priority date	Nov 26, 2012
Publication date	Apr 20, 2017
Grant date	—

Abstract

Apparatus and systems provide for the construction of wing sections having multi-box wing spars. According to one aspect of the disclosure provided herein, an aircraft wing includes multi-box wing spars attached to an aircraft fuselage, an upper wing surface, a lower wing surface, and a number of wing segments. The multi-box wing spars, upper wing surface, and lower wing surface are composite layers having continuous fibers.

First claim

What is claimed is:

1 . A wing, comprising:
a plurality of multi-box wing spars attached to at least one beam of an aircraft fuselage; an upper wing surface; a lower wing surface; and a plurality of wing segments, wherein the plurality of multi-box wing spars, upper wing surface, and lower wing surface are composite layers comprising substantially continuous fibers.

2 . The wing of claim 1 , wherein the wing further comprises a plurality of ribs disposed within the plurality of multi-box wing spars.

3 . The wing of claim 1 , wherein the wing further comprises a leading wing edge and a trailing wing edge comprising composite layers co-cured with the plurality of multi-box wing spars, upper wing surface, and lower wing surface.

4 . The wing of claim 1 , wherein at least one of the multi-box wing spars comprises an elliptical aperture.

5 . The wing of claim 4 , wherein an outer surface of the elliptical aperture is proximate to an inside surface of the aircraft fuselage.

6 . The wing of claim 4 , wherein foci of the elliptical aperture provide an angular displacement between the aircraft fuselage and the wing, wherein the angular displacement provides for a straight-wing or swept-wing profile.

7 . The wing of claim 1 , wherein at least one of the plurality of multi-box wing spars is attached to at least one of a plurality of multi-box wing spars of a second wing.

8 . The wing of claim 1 , further comprising a wing skin co-cured with the plurality of multi-box wing spars.

9 . The wing of claim 1 , wherein the composite layers comprising substantially continuous fibers are co-cured or co-bonded composite layers.

10 . A system for forming an aircraft wing, comprising:
a plurality of mandrels comprising:
an upper surface shaped according to an upper surface of the aircraft wing;
a lower surface shaped according to a lower surface of the aircraft wing; and
a forward surface and an aft surface abutted with one or more of the plurality of mandrels;
a compression apparatus for mechanically curing the one or more layers of composite material forming the aircraft wing, the compression apparatus comprising:
an aft skin surface tool for applying pressure to the aft surface of the plurality of mandrels;
a top skin surface tool for applying pressure to the upper surface of the plurality of mandrels;
a lower skin surface tool for applying pressure to the lower surface of the plurality of mandrels; and
a forward skin surface tool for applying pressure to the forward surface of the plurality of mandrels.

11 . The system of claim 10 , further comprising a heating element for thermally curing the one or more layers of composite material forming the aircraft wing.

12 . The system of claim 10 , further comprising a tension block for maintaining tension on one or more layers of composite material forming the aircraft wing.

13 . A fuselage section of an aircraft, comprising:
a pair of aircraft wings, each aircraft wing comprising
a plurality of multi-box wing spars comprising an elliptical aperture,
an upper wing surface, and
a lower wing surface,
wherein the plurality of multi-box wing spars, upper wing surface, and lower wing surface are composite layers comprising substantially continuous fibers, and wherein the elliptical aperture of each multi-box wing spar defines an interior space of the fuselage section of the aircraft.

14 . The fuselage section of claim 13 , wherein each aircraft wing further comprises a plurality of ribs disposed within the plurality of multi-box wing spars.

15 . The fuselage section of claim 13 , wherein each aircraft wing further comprises a leading wing edge and a trailing wing edge comprising composite layers co-cured with the plurality of multi-box wing spars, upper wing surface, and lower wing surface.

16 . The fuselage section of claim 13 , wherein an outer surface of the elliptical aperture is proximate to an inside surface of the fuselage section.

17 . The fuselage section of claim 13 , wherein foci of the elliptical aperture provide an angular displacement between the fuselage section and the wing, wherein the angular displacement provides for a straight-wing or swept-wing profile.

18 . The fuselage section of claim 13 , wherein at least one of the plurality of multi-box wing spars is attached to at least one of a plurality of multi-box wing spars of a second wing of the pair of aircraft wings.

19 . The fuselage section of claim 13 , further comprising a wing skin co-cured with the plurality of multi-box wing spars.

20 . The fuselage section of claim 13 , wherein the composite layers comprising substantially continuous fibers are co-cured or co-bonded composite layers.

Assignees

• Boeing Co

Inventors

• Moselage Iii John H

Classifications

• B29L2031/3085

  Wings · CPC title

• B64C3/185 Primary

  Spars · CPC title

• B29C70/347

  combined with compressing after the winding of lay-ups having a non-circular cross-section, e.g. flat spiral windings · CPC title

• B64F5/10 Primary

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

• B64C3/20

  Integral or sandwich constructions · CPC title