SELF-SUPPORTING CABIN STRUCTURE

• US 20090250554A1
• Filed: 04/08/2009
• Published: 10/08/2009
• Est. Priority Date: 10/12/2006
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Deutschland GmbH (Airbus SE)
• Inventors: GROSSE-PLANKERMANN, Peter, GRAEBER, Ulrike, PAETZ, Martin
• Granted Patent: US 9,387,920 B2
• Time in Patent Office: Days
• US Class Current: 244/120
• CPC Class Codes: B64C 1/06 Frames; Stringers; Longerons ; Fuselage sections
• CPC Class Codes: B64C 1/066 Interior liners
• CPC Class Codes: B64C 1/068 Fuselage sections
• CPC Class Codes: B64C 2211/00 Modular constructions of airplanes or helicopters
• CPC Class Codes: B64D 2011/0046 Modular or preassembled units for creating cabin interior structures
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 29/49826 Assembling or joining

Abstract

A cabin structural unit for attaching cabin installation elements is provided for an aircraft. The cabin structural unit is set up in such a way that a cabin installation element is attachable. The cabin structural unit is implemented as self-supporting and fastenable to an aircraft structure.

Claims

1. A cabin structural unit for attaching cabin installation elements for an aircraft, comprising:

a cabin installation element;

wherein the cabin structural unit is adapted for attaching the cabin installation element;

wherein the cabin structural unit is adapted for being self-supporting; and

wherein the cabin structural unit is fastenable to an aircraft structure.

2. The cabin structural unit of claim 1;

further comprising a loose bearing device, wherein the cabin structural unit is adapted for being fastened to the aircraft structure using the loose bearing device, so that the cabin structural unit is displaceable along an aircraft longitudinal direction.

3. The cabin structural unit of claim 1;

further comprising a fixed bearing device, wherein the cabin structural unit is fastenable to the aircraft structure by using the fixed bearing device for transmitting forces along an aircraft longitudinal axis.

4. The cabin structural unit of claim 1;

further comprising a damping element, wherein the cabin structural unit is adapted to be fastened to the aircraft structure using the damping element for damping oscillations of the aircraft structure.

5. The cabin structural unit of claim 1;

further comprising;

a plurality of support frames; and

a longitudinal stiffening rib,

wherein the longitudinal stiffening rib is installed between each of the plurality of support frames, and

wherein the longitudinal stiffening rib is adapted for transmitting a force along an aircraft longitudinal axis.

6. The cabin structural unit of claim 1;

further comprising a fastener, wherein the cabin installation element is replaceably fastenable to the cabin structural unit using the fastener.

7. The cabin structural unit of claim 1, wherein the cabin installation element is adapted for being formed integrally and in one piece with the cabin structural unit.

8. The cabin structural unit of claim 1, wherein the cabin installation element is adapted to be installed on the cabin structural unit for transmitting a force flux.

9. The cabin structural unit of claim 1, wherein the cabin structural unit comprises a stiffening face.

10. The cabin structural unit of claim 9, wherein support frames of a plurality of support frames comprising a plurality of support elements, and wherein the plurality of support elements are removably fastenable to one another.

11. The cabin structural unit of claim 10;

wherein the plurality of support elements are removably fastenable to one another using a plug-in connection.

12. The cabin structural unit of claim 1;

wherein the aircraft structure comprises a floor structure and the cabin structural unit is fastenable to the floor structure.

13. The cabin structural unit of claim 1;

wherein the cabin installation element is selected from the group consisting of toilet units, kitchen units, seat units, design elements, stairway elements, baggage compartments, air provision units or elevator units.

14. The cabin structural unit of claim 1, further comprising:

cabin structural segments; and

hinges, wherein the cabin structural segments are connected by the hinges for being foldable.

15. The cabin structural unit of claim 12, wherein the cabin structural unit further comprises interface elements;

and the interface elements are adapted to connect the cabin installation elements with at least one of the aircraft structure or the floor structure.

16. The cabin structural unit of claim 1, wherein the cabin structural unit is adapted for supporting the aircraft structure.

17. A cabin system for attaching cabin installation elements;

wherein the cabin system comprises;

a first cabin structural unit, comprising a first cabin installation element, wherein the first cabin structural unit is adapted for attaching the first cabin installation element, wherein the first cabin structural unit is adapted for being self-supporting, and wherein the first cabin structural unit is fastenable to an aircraft structure;

a second cabin structural unit, comprising a second cabin installation element, wherein the second cabin structural unit is adapted for attaching the second cabin installation element, wherein the second cabin structural unit is adapted for being self-supporting, and wherein the second cabin structural unit is fastenable to the aircraft structure; and

a compensation element, wherein the compensation element is adapted for being installed between the first cabin structural unit and the second cabin structural unit for compensating tolerances.

18. A method for attaching cabin installation elements for an aircraft;

wherein the method comprising the steps of;

fastening a cabin installation element to a cabin structural unit; and

fastening the cabin structural unit to an aircraft structure, wherein the cabin structural unit is adapted for being self-supporting.

19. The method of claim 18, wherein the cabin installation element is attached to the cabin structural unit in a first step and the cabin structural unit comprising the cabin installation element is fastened to the aircraft structure in a second step that follows the first step.

20. A method for installing a cabin structural unit for an aircraft, the method comprising the steps of:

pre-assembling the cabin structural unit outside of an aircraft structure;

guiding a pre-assembled cabin structural unit through an opening of the aircraft structure;

implementing the pre-assembled cabin structural unit to a predetermined location in the aircraft structure; and

fixing the pre-assembled cabin structural unit at the predetermined location in the aircraft structure.

21. The method of claim 20;

wherein the pre-assembled cabin structural unit is adapted for being foldable, and the method further comprises the steps of;

folding the pre-assembled cabin structural unit before guiding the pre-assembled cabin structural unit through the opening of the aircraft structure; and

unfolding the pre-assembled cabin structural unit at the predetermined location in the aircraft structure.

22. The method of claim 20;

further comprising the step of installing a cabin installation element into the pre-assembled cabin structural unit outside of the aircraft structure.

23. The method of claim 20 wherein the opening of the aircraft structure is selected from one of the group consisting of fuselage doors, openings of fuselage segments and cargo doors.