Aerodynamic component and method for producing an aerodynamic component

Patent metadata

Field	Value
Publication number	US-9745053-B2
Application number	US-201514937220-A
Country	US
Kind code	B2
Filing date	Nov 10, 2015
Priority date	Nov 11, 2014
Publication date	Aug 29, 2017
Grant date	Aug 29, 2017

Abstract

An aerodynamic component which in particular is suitable for use in an aircraft includes an outer skin sheet having an inner surface and an outer surface and being provided with perforation openings allowing a flow of air therethrough. The outer surface of the outer skin sheet forms an aerodynamic surface of the aerodynamic component. The aerodynamic component further includes a sandwich panel which includes an outer layer facing the inner surface of the outer skin sheet, an inner layer facing away from the inner surface of the outer skin sheet and a foam core sandwiched between the outer layer and the inner layer. The sandwich panel is provided with connection openings extending through the sandwich panel between the outer layer and the inner layer and allowing a flow of air therethrough.

First claim

The invention claimed is:

1. An aerodynamic component for use on an aircraft, the component comprising:
an outer skin sheet having an inner surface and an outer surface and being provided with a plurality of perforation openings allowing a flow of air therethrough, wherein the outer surface of the outer skin sheet forms an aerodynamic surface of the aerodynamic component; and
a sandwich panel including:
an outer layer facing the inner surface of the outer skin sheet,
an inner layer facing away from the inner surface of the outer skin sheet,
a foam core sandwiched between the outer layer and the inner layer,
a plurality of connection openings each extending through the foam core, the outer layer and the inner layer and allowing a flow of air through the sandwich panel, and
in a surface of the sandwich panel facing the outer skin sheet, a plurality of surface channels extending across the surface and connecting the perforation openings in the outer skin sheet to the connection openings extending through the sandwich panel.

2. The aerodynamic component according to claim 1 , wherein the outer skin sheet is made of a metallic material, selected from the group of: titanium, a titanium alloy, a corrosion resistant steel alloy or an aluminum alloy.

3. The aerodynamic component according to claim 1 , wherein at least one of the inner and the outer layer of the sandwich panel is made of a fiber reinforced composite material, selected from the group of: a carbon fiber or glass fiber reinforced plastic material.

4. The aerodynamic component according to claim 1 , wherein the surface channels extend substantially parallel to each other across the surface of the sandwich panel.

5. The aerodynamic component according to claim 1 , wherein the connection openings open into the surface channels in the region of an apex of the surface channels.

6. The aerodynamic component according to claim 1 , wherein the plurality of surface channels extending across the surface of the sandwich panel are separated from each other by attachment portions which support the outer skin sheet of the aerodynamic component.

7. The aerodynamic component according to claim 1 , further comprising at least one of:
a reinforced edge region extending along at least a portion of a circumference of the inner layer of the sandwich panel;
an inner reinforcement sheet arranged between the inner layer and the foam core of the sandwich panel; and
an outer reinforcement sheet arranged between the foam core and the outer layer of the sandwich panel.

8. A method for producing an aerodynamic component for use on an aircraft, the method comprising:
providing an outer skin sheet having an inner surface and an outer surface and being provided with a plurality of perforation openings allowing a flow of air therethrough, wherein the outer surface of the outer skin sheet is adapted to form an aerodynamic surface of the aerodynamic component; and
providing a sandwich panel which includes an outer layer, an inner layer and a foam core sandwiched between the outer layer and the inner layer;
forming a plurality of connection openings in the sandwich panel which each extend through the foam core, the outer layer, and the inner layer and allow a flow of air through the sandwich panel;
providing a plurality of surface channels extending across a surface of the outer layer of the sandwich panel; and
attaching the outer skin sheet to the sandwich panel such that:
the outer layer of the sandwich panel faces the inner surface of the outer skin sheet,
the inner layer of the sandwich panel faces from the inner surface of the outer skin sheet, and
the plurality of surface channels fluidly connect the perforation openings provided in the outer skin sheet to the connection openings extending through the sandwich panel.

9. The method according to claim 8 , wherein the outer skin sheet is made of a metallic material, selected from a group consisting of titanium, a titanium alloy, a corrosion resistant steel alloy and an aluminum alloy.

10. The method according to claim 8 , wherein at least one of the inner and the outer layer of the sandwich panel is made of a fiber reinforced composite material, selected from a group consisting of a carbon fiber and glass fiber reinforced plastic material.

11. The method according to claim 8 , wherein the surface channels extend substantially parallel to each other across the sandwich panel and wherein the connection openings open into the surface channels in a region of an apex of the surface channels.

12. The method according to claim 8 , wherein the outer skin sheet of the aerodynamic component is attached to attachment portions of the sandwich panel which separate the plurality of surface channels extending across the surface of the sandwich panel from each other.

13. The method according to claim 8 , further comprising at least one of:
applying the inner layer as a semi-finished inner layer to a surface of a positive preform tool;
applying the foam core onto the semi-finished inner layer;
applying the outer layer as a semi-finished outer layer onto the foam core;
moving the layer arrangement comprising the semi-finished inner layer, the foam core and the semi-finished outer layer from the positive preform tool into a negative forming tool in such a manner that an outer surface of the semi-finished outer layer which faces away from the foam core is in contact with a forming surface of the forming tool;
injecting a curable material into the semi-finished inner layer and the semi-finished outer layer;
curing the curable material injected into the semi-finished inner layer and the semi-finished outer layer so as to provide the inner layer and the outer layer of the sandwich panel;
removing the sandwich panel from the forming tool; or
forming the connection openings by drilling into the sandwich panel.

14. The method according to claim 13 , wherein core elements are arranged in at least one of the forming tool and the layer arrangement which are received within the surface channels when the layer arrangement is arranged in the forming tool so as to force the semi-finished outer layer against the foam core.

15. The method according to claim 13 , further comprising at least one of:
applying a semi-finished reinforced edge region to the surface of the positive preform tool which extends along at least a portion of a circumference of the semi-finished inner layer;
arranging a semi-finished inner reinforcement sheet between the semi-finished inner layer and the foam core;
arranging a semi-finished outer reinforcement sheet between the foam core and the semi-finished outer layer;
injecting a curable material into at least one of the semi-finished reinforced edge region, the semi-finished inner reinforcement sheet and the semi-finished outer reinforcement sheet; or
curing the curable material to provide at least one of a reinforced edge region extending along at least a portion of a circumference of the inner layer of the sandwich panel, an inner reinforcement sheet arranged between the inner layer and the foam core of the sandwich panel and an outer reinforcement sheet arranged between the foam core and the outer layer of the sandwich panel.

Assignees

• Airbus Operations Gmbh

Inventors

• Teich Benjamin

Classifications

• B64C3/20 Primary

  Integral or sandwich constructions · CPC title

• B64C2230/08

  by influencing fluid flow by means of surface cavities, i.e. net fluid flow is null · CPC title

• B64C2230/04

  by actively generating fluid flow · CPC title

• B64C21/06 Primary

  for sucking (BLI propulsion B64C21/01) · CPC title

• B64F5/10

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