SUPPORT STRUCTURE FOR A WING

• US 20100170995A1
• Filed: 08/16/2006
• Published: 07/08/2010
• Est. Priority Date: 08/17/2005
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Deutschland GmbH (Airbus SE)
• Inventors: Maenz, Christian
• Granted Patent: US 8,205,834 B2
• Time in Patent Office: Days
• US Class Current: 244/131
• CPC Class Codes: B64C 1/26 Attaching the wing or tail units or stabilising surfaces
• CPC Class Codes: B64C 3/00 Wings ornithopter wings B64C33/02
• CPC Class Codes: B64C 3/26 Construction, shape, or attachment of separate skins, e.g. panels
• CPC Class Codes: B64C 5/06 Fins B64C5/08 takes precedence
• CPC Class Codes: E04B 2001/193 with flattened connecting parts, e.g. ends

Abstract

A support structure for an aircraft, includes one or several bar elements and one or several junction elements. At least one bar element includes a transition region which can be made to engage at least one junction element. When the transition region of the bar element engages at least one junction element, centric force transmission takes place between the bar element and the junction element.

Claims

1. A support structure for an aircraft, comprising:

at least one bar element; and

at least one junction element;

wherein the at least one bar element comprises a transition region;

the transition region comprises a first end with a first cross-sectional shape and a second end with a second cross-sectional shape with the first and the second cross-sectional shapes being different; and

the second end of the transition region is shaped as a symmetric flattening of a tube, and the transition region is engageable with the at least one junction element such that there is at least partial overlap, and the transition region of the at least one bar element is shaped such that when the transition region engages the at least one junction element, a force is centrically transmitted between the at least one bar element and the at least one junction element.

2. The support structure of claim 1,

wherein the first end of the transition region comprises a substantially round cross-sectional shape.

3. The support structure of claim 1,

wherein the at least one bar element comprises a substantially tubular cross-sectional shape.

4. The support structure of claim 1,

wherein the second end of the transition region comprises a beak shape.

5. The support structure of claim 1,

wherein the transition region is designed as a connection element;

and

the connection element is separatable from the at least one bar element.

6. The support structure of claim 5,

wherein the connection element is a one-piece connection element.

7. The support structure of claim 5,

wherein the connection element includes a plurality of parts.

8. The support structure of claim 1,

wherein the at least one junction element is shaped to engage the transition region of the at least one bar element.

9. The support structure of claim 1,

wherein the at least one junction element comprises:

at least one attachment element; and

a reference face;

and the at least one attachment element is connected to the reference face such that a spatial direction for the at least one bar element is defined by an angle between the attachment element and the reference face.

10. The support structure of claim 1,

wherein the junction element is an airframe element.

17. A junction element for the support structure of claim 1, comprising:

at least one attachment element;

wherein the attachment element is shaped to engage a connection element or a transition region of a bar element or both so as to at least partially overlap.

18. The junction element of claim 17, further comprising:

a reference face;

wherein the at least one attachment element is connected to the reference face such that a spatial direction for a connectable bar element or connection element or both may be defined by an angle between the attachment element and the reference face.

19. The junction element of claim 17,

wherein the junction element is an airframe element.

20. A wing comprising a support structure of claim 1.

22. A wing comprising

a junction element of claim 17.

26. An aircraft comprising the support structure of claim 1.

11. A connection element for a support structure, comprising:

a basic body;

wherein the basic body comprises a first end,

the first end is capable of connecting to a bar element,

the basic body comprises a second end,

the second end is engageable with a junction element so as to at least partly overlap;

the first end of the connection element comprises a first cross-sectional shape,

the second end of the connection element comprises a second cross-sectional shape,

the first cross-sectional shape and the second cross-sectional shape are different; and

the second end of the connection element is shaped as an asymmetric flattening of a tube, and the basic body is shaped in such a way that when the connection element engages the junction element, a force is centrically transmitted between the bar element and the junction element.

12. The connection element of claim 11,

wherein the first end of the connection element defines an internal shape such that a bar element with substantially round cross-sectional shape is connectable to the internal shape of the first end.

13. The connection element of claim 11,

wherein the first end of the connection element defines an internal shape such that a bar element with a substantially tubular cross-sectional shape is connectable to the internal shape of the first end.

14. The connection element of claim 11,

wherein the second end of the connection element comprises a beak shape.

15. The connection element of claim 11,

wherein the connection element is an one piece connection element.

16. The connection element of claim 11,

wherein the connection element includes several parts.

21. A wing comprising a connection element of claim 11.

23. A method for the transmission of forces between a bar element and a junction element by a connection element, wherein the method comprises:

connecting the bar element to a first end of a basic body of the connection element;

at least partially overlapping a connection of the junction element to a second end of the basic body of the connection element;

centrically transmitting a force between the bar element and the junction element;

accommodating the force that acts in a first cross section;

transferring the force, for centric introduction of the force into a second cross section; and

centrically introducing the force into a second cross section;

wherein the first cross section and the second cross section differ from each other;

and wherein the second end of the basic body is shaped as a symmetric flattening of a tube.

24. The method of claim 23, further comprising:

a step of accommodating the force on a round cross section.

25. The method of claim 23, further comprising:

a step of accommodating the force on a tubular cross section.