Aircraft structure component for laminar flow

Patent metadata

Field	Value
Publication number	US-10836471-B2
Application number	US-201715799336-A
Country	US
Kind code	B2
Filing date	Oct 31, 2017
Priority date	Nov 16, 2016
Publication date	Nov 17, 2020
Grant date	Nov 17, 2020

Abstract

An aircraft structure component for laminar flow, the aircraft structure component having an outer skin with an aerodynamic surface, wherein the aerodynamic surface has a leading edge portion and a downstream portion adjacently downstream from the leading edge portion, and wherein the downstream portion of the aerodynamic surface includes a paint layer that is not present in the leading edge portion, so that an edge line is formed between the leading edge portion and the downstream portion by the beginning paint layer. An object, to provide an aircraft structure component that allows for a reduced aerodynamic drag, is achieved in that the edge line has a ramp-shaped cross section, wherein the thickness of the paint layer increases from a starting point over a predetermined ramp length to a saturation point where the full thickness of the paint layer is reached.

First claim

The invention claimed is:

1. An aircraft structure component for laminar flow, the aircraft structure component having an outer skin with an aerodynamic surface,
wherein the aerodynamic surface has a leading edge portion and a downstream portion adjacently downstream from the leading edge portion, and
wherein the downstream portion of the aerodynamic surface comprises a paint layer or a foil layer that is not present in the leading edge portion, so that an edge line is formed between the leading edge portion and the downstream portion by the beginning paint layer or foil layer, and
wherein the edge line has a ramp-shaped cross section, wherein a thickness of the paint layer or foil layer increases from a starting point over a predetermined ramp length to a saturation point where a full thickness of the paint layer or foil layer is reached.

2. The aircraft structure component according to claim 1 , wherein the ramp length is at least as great as the full thickness of the paint layer or foil layer at the saturation point.

3. The aircraft structure component according to claim 1 , wherein the ramp-shaped cross section of the edge line has a linear course, so that thickness of the paint layer or foil layer increases linearly from the starting point to the saturation point.

4. The aircraft structure component according to claim 1 , wherein the ramp-shaped cross section of the edge line has a curved course, so that the thickness of the paint layer or foil layer increases nonlinearly from the starting point to the saturation point with an increasing slope or a decreasing slope.

5. The aircraft structure component according to claim 4 , wherein the ramp-shaped cross section of the edge line has a double-curved course, so that the thickness of the paint layer or foil layer increases from the starting point to the saturation point with an increasing slope followed by a decreasing slope.

6. The aircraft structure component according to claim 1 , wherein the edge line has a straight course along the aerodynamic surface.

7. The aircraft structure component according to claim 6 , wherein an angle between the course of the edge line and a direction of incoming flow is greater than 30°.

8. The aircraft structure component according to claim 1 , wherein the edge line has a periodically curved course along the aerodynamic surface.

9. The aircraft structure component according to claim 8 , wherein the edge line has a sinusoidal course along the aerodynamic surface.

10. The aircraft structure component according to claim 8 , wherein an angle between a direction of incoming flow and a tangent to an inflection point present in the course of the edge line, is greater than 30°.

11. The aircraft structure component according to claim 8 , wherein all angles between a direction of incoming flow and tangents to the inflection points present in the course of the edge line are equal.

12. The aircraft structure component according to claim 8 , wherein the course of the edge line defines a plurality of fore peaks and a plurality of aft peaks with respect to a direction of the incoming flow,
wherein, while at an aft peak the ramp length is as great as full thickness of the paint layer or foil layer at the saturation point, at an adjacent fore peak the ramp length is between twice and 20 times as great as full thickness of the paint layer or foil layer at the saturation point.

13. The aircraft structure component according to claim 12 , wherein, while at an aft peak the ramp length is as great as the full thickness of the paint layer or foil layer at the saturation point, at an adjacent fore peak the ramp length is between 5 and 10 times as great as the full thickness of the paint layer or foil layer at the saturation point.

14. A method for producing an aircraft structure component for laminar flow, the method comprising:
providing an aircraft structure component having an outer skin with an aerodynamic surface, wherein the aerodynamic surface has a leading edge portion and a downstream portion adjacently downstream from the leading edge portion;
applying a paint layer or foil layer onto the downstream portion of the aerodynamic surface without applying the paint layer or foil layer also to the leading edge portion, so that an edge line is formed between the leading edge portion and the downstream portion by the beginning paint layer or foil layer; and
processing the paint layer or foil layer along the edge line, such that the edge line has a ramp-shaped cross section, wherein a thickness of the paint layer or foil layer increases from a starting point over a predetermined ramp length to a saturation point where the full thickness of the paint layer or foil layer is reached.

15. The method according to claim 14 , wherein the paint layer or foil layer is processed along the edge line by removing material of the paint layer or foil layer.

16. The method according to claim 15 , wherein the material of the paint layer or foil layer is removed by grinding, polishing, or laser treatment.

17. The method according to claim 16 , wherein the laser treatment comprises laser ablation.

Assignees

• Airbus Operations Gmbh

Inventors

• Schlipf Bernhard
• Daandels Dort

Classifications

• B64C23/005 Primary

  by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds · CPC title

• B05D3/12

  by mechanical means · CPC title

• B05D3/007

  After-treatment · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64C2230/00

  Boundary layer controls · CPC title