Aircraft wings, aircraft, and related methods

Patent metadata

Field	Value
Publication number	US-2018099736-A1
Application number	US-201615291859-A
Country	US
Kind code	A1
Filing date	Oct 12, 2016
Priority date	Oct 12, 2016
Publication date	Apr 12, 2018
Grant date	—

Abstract

Aircraft wings, aircraft, and related methods. Aircraft wings include a spoiler constructed substantially of a monolithic structural body with an upper side that defines a portion of an airfoil surface of an aircraft wing. The monolithic structural body further includes a lower side, opposite the upper side, that includes a plurality of stiffening ribs that define a plurality of open voids. Methods of constructing a spoiler for an aircraft wing include forming a monolithic structural body of the spoiler.

First claim

1 . An aircraft, comprising:
a fuselage; and an aircraft wing operatively coupled to the fuselage, wherein the aircraft wing comprises:
an outboard wing box constructed substantially of a composite material;
a spoiler operatively coupled to the outboard wing box, wherein the spoiler is constructed substantially of a metallic monolithic structural body, wherein the metallic monolithic structural body includes:
an upper side that defines a portion of an airfoil surface of the aircraft wing when the spoiler is in a stowed position; and
a lower side, opposite the upper side, that includes a plurality of stiffening ribs that define a plurality of open voids;

at least one spoiler deployment mechanism operatively coupled between the spoiler and the outboard wing box and configured to operatively deploy and stow the spoiler;
a flap operatively coupled to the outboard wing box at least partially below and partially rearward of the spoiler, wherein the flap is constructed substantially of a composite material; and
at least one flap deployment mechanism operatively coupled between the flap and the outboard wing box and configured to operatively deploy and stow the flap.

2 . An aircraft wing, comprising:
a spoiler constructed substantially of a monolithic structural body wherein the monolithic structural body includes:
an upper side that defines a portion of an airfoil surface of the aircraft wing when the spoiler is in a stowed position; and
a lower side, opposite the upper side, that includes a plurality of stiffening ribs that define a plurality of open voids.

3 . The aircraft wing of claim 2 , wherein the monolithic structural body is constructed substantially of an aluminum alloy.

4 . The aircraft wing of claim 2 , wherein the monolithic structural body is at least one of a machined structural body and a 3D-printed structural body.

5 . The aircraft wing of claim 2 , wherein the spoiler is devoid of honeycomb core structures and sandwich panels.

6 . The aircraft wing of claim 2 , wherein the spoiler is devoid of a skin that extends across the plurality of stiffening ribs to define a lower surface of the spoiler.

7 . The aircraft wing of claim 2 , wherein the plurality of open voids includes at least one of:
a first subset of open voids that have triangular profiles when viewed from below; and a second subset of open voids that have quadrilateral profiles when viewed from below.

8 . The aircraft wing of claim 2 , wherein the monolithic structural body defines at least one integral lug configured for attachment to one or more respective spoiler deployment mechanisms.

9 . The aircraft wing of claim 8 , wherein at least one of the at least one integral lug is positioned such that at least one of the plurality of open voids is positioned and sized to receive at least a portion of a spoiler deployment mechanism of the one or more respective spoiler deployment mechanisms when the spoiler is stowed.

10 . The aircraft wing of claim 2 , wherein the monolithic structural body includes an upper surface, wherein the upper surface includes a forward region and an aft region rearward of the forward region, wherein the forward region is configured to match the airfoil surface of the aircraft wing when the spoiler is stowed, and wherein the aft region is configured to match the airfoil surface of the aircraft wing responsive to a cruise pressure applied to the aircraft wing and when the spoiler is stowed.

11 . The aircraft wing of claim 10 , wherein the forward region and the aft region are separated by a parabolic boundary.

12 . The aircraft wing of claim 2 , wherein the spoiler further comprises a flexible trailing edge structure coupled to the monolithic structural body along an aft edge of the monolithic structural body.

13 . The aircraft wing of claim 2 , wherein the spoiler further comprises side seals coupled to the monolithic structural body along lateral sides of the monolithic structural body, wherein the side seals are constructed of a coated fabric material.

14 . The aircraft wing of claim 2 , wherein the aircraft wing further includes:
an outboard wing box constructed substantially of a composite material, wherein the spoiler is operatively coupled to the outboard wing box; at least one spoiler deployment mechanism operatively coupled between the spoiler and the outboard wing box and configured to operatively deploy and stow the spoiler; a flap operatively coupled to the outboard wing box at least partially below and partially rearward of the spoiler, wherein the flap is constructed substantially of a composite material; and at least one flap deployment mechanism operatively coupled between the flap and the outboard wing box and configured to operatively deploy and stow the flap; wherein the monolithic structural body is metallic.

15 . The aircraft wing of claim 14 , wherein the flap is configured as a fowler flap.

16 . The aircraft wing of claim 14 ,
wherein the spoiler has a deployed spoiler position and a range of stowed spoiler positions, wherein in the deployed spoiler position, a trailing edge of the spoiler is pivoted upward and away from the flap; wherein the flap has a stowed flap position and a range of deployed flap positions, wherein in the range of deployed flap positions, a trailing edge of the flap is one or both of translated rearward and pivoted downward relative to the spoiler; and wherein, when the spoiler is in the range of stowed spoiler positions, the trailing edge of the spoiler is engaged with the flap when the flap is in the stowed flap position and when the flap is in at least a subset of the range of deployed flap positions.

17 . The aircraft wing of claim 16 ,
wherein the monolithic structural body comprises a flap contact surface positioned at a rearward edge region of the monolithic structural body; and wherein the flap contact surface is positioned to be engaged by the flap when the flap transitions from the range of deployed flap positions to the stowed flap position to cause the trailing edge of the spoiler to pivot upward.

18 . The aircraft wing of claim 16 , wherein the aircraft wing is configured to restrict airflow between the spoiler and the flap when the spoiler is in the range of stowed spoiler positions and when the flap is in the stowed flap position.

19 . An aircraft, comprising:
a fuselage; and the aircraft wing of claim 2 operatively coupled to the fuselage.

20 . A method of constructing a spoiler for an aircraft wing, the method comprising:
forming a monolithic structural body of the spoiler, wherein the monolithic structural body has an upper side that defines a portion of an airfoil surface of the aircraft wing when the spoiler is stowed and a lower side, opposite the upper side, that includes a plurality of stiffening ribs that define a plurality of open voids; wherein the forming includes at least one of machining and 3D printing.

Assignees

• Boeing Co

Inventors

• Kordel Jan A
• Balzer Michael Albert
• Burton Jeffrey
• Walker Steven Paul
• Saunders John Barry

Classifications

• B64C3/187

  Ribs · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• B64C2009/143

  comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps · CPC title

• B64C3/58 Primary

  provided with fences or spoilers (adjustable for control purposes B64C9/00) · CPC title

• B33Y10/00

  Processes of additive manufacturing · CPC title