Floor arrangement for a cabin of a vehicle

Patent metadata

Field	Value
Publication number	US-10940934-B2
Application number	US-201816123472-A
Country	US
Kind code	B2
Filing date	Sep 6, 2018
Priority date	Sep 12, 2017
Publication date	Mar 9, 2021
Grant date	Mar 9, 2021

Abstract

A floor arrangement for a cabin of a vehicle, in particular of an aircraft or spacecraft, comprises a carrier plate formed with a multiplicity of first fastening perforations and a multiplicity of reinforcing notches. The first fastening perforations are arranged one behind another in fastening rows at a uniform longitudinal distance. The fastening rows are oriented parallel at a uniform transverse distance from one another at an angle of orientation of 45° with respect to a longitudinal direction of the floor arrangement. The reinforcing notches run along the angle of orientation in a manner offset with respect to the fastening rows. A floor panel is formed with a multiplicity of second fastening perforations and is arranged above the carrier plate such that the second fastening perforations are arranged above the first fastening perforations to fasten cabin elements through the floor panel to the carrier plate.

First claim

The invention claimed is:

1. A floor arrangement for a cabin of a vehicle, comprising:
a carrier plate formed with a multiplicity of first fastening perforations and a multiplicity of reinforcing notches,
wherein the first fastening perforations are arranged one behind another in fastening rows at a uniform longitudinal distance,
wherein the fastening rows are oriented parallel at a uniform transverse distance from one another at an angle of orientation of 45° with respect to a longitudinal direction of the floor arrangement, and
wherein the reinforcing notches run along the angle of orientation in a manner offset with respect to the fastening rows; and

a floor panel formed with a multiplicity of second fastening perforations and being arranged above the carrier plate such that the second fastening perforations are arranged above the first fastening perforations to fasten cabin elements through the floor panel to the carrier plate.

2. The floor arrangement according to claim 1 , further comprising a multiplicity of bearers under the carrier plate, which bearers support the carrier plate on the reinforcing notches.

3. The floor arrangement according to claim 1 , wherein the carrier plate is formed as a plate made from a metal material.

4. The floor arrangement according to claim 1 , wherein the carrier plate is formed as a plate made from a fiber-reinforced plastic component.

5. The floor arrangement according to claim 1 , wherein the reinforcing notches are formed with a multiplicity of function perforations.

6. The floor arrangement according to claim 5 , wherein the function perforations are oriented along the longitudinal direction of the floor arrangement.

7. The floor arrangement according to claim 1 , wherein the first fastening perforations and the second fastening perforations are configured to receive ball lock pins.

8. The floor arrangement according to claim 7 , further comprising a multiplicity of washers under the carrier plate with third fastening perforations for fastening the ball lock pins.

9. The floor arrangement according to claim 7 , further comprising a multiplicity of underlay strips under the carrier plate with third fastening perforations for fastening the ball lock pins.

10. The floor arrangement according to claim 1 , wherein the carrier plate is configured with a multiplicity of secondary reinforcing notches which run along the angle of orientation parallel to the reinforcing notches.

11. The floor arrangement according to claim 1 , wherein the first fastening perforations are arranged in such a manner that a uniform perforation distance of the first fastening perforations in the longitudinal direction of the floor arrangement and in a transverse direction of the floor arrangement is produced from an integral multiple of one inch.

12. The floor arrangement according to claim 11 , wherein the perforation distance of the first fastening perforations in the longitudinal direction and the transverse direction of the floor arrangement is 3 inches.

13. The floor arrangement according to claim 1 , wherein the longitudinal distance of the first fastening perforations in the fastening rows is √2 inches.

14. The floor arrangement according to claim 1 , wherein the transverse distance of the fastening rows is between 2 inches and 3 inches.

15. The floor arrangement according to claim 1 , further comprising a further carrier plate configured identically to the carrier plate, wherein the two carrier plates are arranged next to each other transversely with respect to the longitudinal direction of the floor arrangement, and wherein the fastening rows and the reinforcing notches of the further carrier plate are oriented rotated by 90° with respect to the fastening rows and the reinforcing notches of the carrier plate such that the fastening rows and the reinforcing notches of the two carrier plates converge in a V-shaped manner.

16. An aircraft or spacecraft with a floor arrangement according to claim 1 .

Assignees

• Airbus Operations Gmbh

Inventors

• Lange Roland
• Heidtmann Andreas

Classifications

• B32B2260/021

  Fibrous or filamentary layer · CPC title

• B32B3/30

  characterised by a layer formed with recesses or projections, e.g. {hollows, grooves, protuberances, ribs (apertured layer B32B3/266; layer with cavities or internal voids B32B3/26)} · CPC title

• B32B7/08

  by mechanical means · CPC title

• B32B2262/101

  Glass fibres · CPC title

• B32B3/10

  characterised by a discontinuous layer, i.e. formed of separate pieces of material · CPC title