Aircraft having an aircraft fuselage and an air sucking fuselage component

Patent metadata

Field	Value
Publication number	US-9623959-B2
Application number	US-201313850353-A
Country	US
Kind code	B2
Filing date	Mar 26, 2013
Priority date	Mar 27, 2012
Publication date	Apr 18, 2017
Grant date	Apr 18, 2017

Abstract

An aircraft having an aircraft fuselage that has an outer skin includes an air sucking fuselage component with an outer surface that is perforated at least in some regions, and a suction profile body. The suction profile body is arranged on the outer skin, forms a local bulge in the outer skin, and further includes a suction opening that is arranged at a location at which there is the lowest pressure, for example at a position furthest away from the outer skin. The suction opening is connected to a suction connection of the air sucking fuselage component. In this way laminarization of the flow at the air sucking fuselage component may take place without the use of active air conveying devices.

First claim

What is claimed is:

1. An aircraft having an aircraft fuselage that has an outer skin, comprising:
an air sucking fuselage component with an outer surface that is perforated at least in some regions; and
a suction profile body arranged on the outer skin on top of a vertical stabilizer or on a bottom of the fuselage, that forms a local three-dimensional rounded bulge on the outer skin bulging outwardly from the outer skin, and including a suction opening that is arranged at a location of the suction profile body at which there is the lowest pressure in an airflow during the flight,
wherein the air sucking fuselage component and the suction profile body are in fluid communication, the suction opening being connected to a suction connection of the air sucking fuselage component.

2. The aircraft of claim 1 , wherein the location of the suction profile body at which the lowest pressure is present during the flight is the location on the suction profile body farthest from the outer skin of the aircraft fuselage.

3. The aircraft of claim 1 , wherein the suction profile body is arranged on the top of the vertical stabilizer.

4. The aircraft of claim 3 , wherein the suction profile body is arranged on an upper delimitation surface of the vertical stabilizer.

5. The aircraft of claim 1 , wherein the suction profile body is arranged on an underside of the aircraft fuselage.

6. The aircraft of claim 5 , wherein the suction profile body follows on upstream of an outlet valve of an air conditioning system.

7. The aircraft of claim 1 , further comprising an air conveying device that is arranged between the suction opening of the suction profile body and the suction connection of the air sucking fuselage component.

8. The aircraft of claim 1 , further comprising a closing device for selectively closing the suction opening of the suction profile body.

9. The aircraft of claim 8 , wherein the closing device is a flap that is movable to a closed position and to at least one open position.

10. The aircraft of claim 8 , wherein the flap is movable to an outward directed position as a deflector in front of the suction opening.

11. The aircraft of claim 1 , wherein the suction opening of the suction profile body has a diameter ranging from 50 mm to 1000 mm.

12. The aircraft of claim 1 , wherein the suction profile body has a droplet shape with a rounded end of the droplet and a pointed end of the droplet, wherein the rounded end of the droplet points in the direction of flight of the aircraft.

13. The aircraft of claim 1 , wherein the outer surface is microperforated, at least in some regions, and comprises holes of a diameter ranging from 25 to 100 μm.

14. The aircraft of claim 13 , wherein the holes are arranged so as to be equidistant from each other, with the distance ranging from 0.1 mm to 10 mm.

15. An aircraft having an aircraft fuselage that has an outer skin, comprising:
an air sucking fuselage component with an outer surface that is perforated at least in some regions;
a suction profile body arranged on the outer skin on to of a vertical stabilizer or on a bottom of the fuselage, that forms a local rounded three-dimensional bulge on the outer skin bulging outwardly from the outer skin, and including a suction opening that is arranged at a location of the suction profile body at which there is the lowest pressure in an airflow during the flight; and
a closing device for selectively closing the suction opening of the suction profile body,
wherein the air sucking fuselage component and the suction profile body are in fluid communication, the suction opening being connected to a suction connection of the air sucking fuselage component.

16. The aircraft of claim 15 , wherein the closing device is a flap that is movable to a closed position and to at least one open position.

17. The aircraft of claim 15 , wherein the flap is movable to an outward directed position as a deflector in front of the suction opening.

18. The aircraft of claim 15 , wherein the suction profile body has a droplet shape with a rounded end of the droplet and a pointed end of the droplet, wherein the rounded end of the droplet points in the direction of flight of the aircraft.

19. The aircraft of claim 15 , wherein the location of the suction profile body at which the lowest pressure is present during the flight is the location on the suction profile body farthest from the outer skin of the aircraft fuselage.

20. The aircraft of claim 15 , wherein the suction profile body is arranged on the to of the vertical stabilizer.

Assignees

• Airbus Operations Gmbh

Inventors

• Schrauf Géza
• Stuke Hubert

Classifications

• Y02T50/10

  Drag reduction · CPC title

• Y02T50/166

  Cross-Sectional Technologies · mapped topic

• B64C5/06 Primary

  Fins (B64C5/08 takes precedence) · CPC title

• B64C21/06 Primary

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