Decompression panel for use in an aircraft assembly

Patent metadata

Field	Value
Publication number	US-9566759-B2
Application number	US-201414471161-A
Country	US
Kind code	B2
Filing date	Aug 28, 2014
Priority date	Oct 25, 2013
Publication date	Feb 14, 2017
Grant date	Feb 14, 2017

Abstract

A decompression panel for use in an aircraft assembly that includes a body portion including a top edge and a bottom edge, and a front surface and a rear surface opposing the front surface. A plurality of openings are formed in the body portion, and a first stiffening member is formed on the rear surface below the plurality of openings. The first stiffening member extends from the rear surface towards the top edge such that the plurality of openings are at least partially obstructed by the first stiffening member.

First claim

What is claimed is:

1. A decompression panel for use in an aircraft assembly, said decompression panel comprising:
a body portion comprising a top edge and a bottom edge, and a front surface and a rear surface opposing said front surface;
a plurality of openings formed in said body portion and extending between said front surface and said rear surface; and
at least one first stiffening member formed on said rear surface below said plurality of openings, said at least one first stiffening member extending along a width of said body portion and at least partially circumscribing at least one opening in said plurality of openings, said at least one first stiffening member further extending from said rear surface towards said top edge such that said plurality of openings are at least partially obstructed by said first stiffening member.

2. The decompression panel in accordance with claim 1 , wherein said plurality of openings are arranged in rows that extend across the width of said body portion, wherein openings in said plurality of openings vary in shape along each of said rows.

3. The decompression panel in accordance with claim 2 , wherein said rows of openings are arranged in at least two groupings that each include two or more rows, wherein adjacent groupings are separated from each other by a distance.

4. The decompression panel in accordance with claim 3 further comprising a baffle tab extending from said rear surface and positioned between said adjacent groupings of rows.

5. The decompression panel in accordance with claim 2 , wherein said at least one first stiffening member comprises a plurality of first stiffening members formed on said rear surface, wherein one of said plurality of first stiffening members extends along the width of said body portion below each row of openings.

6. The decompression panel in accordance with claim 1 , wherein said at least one first stiffening member at least partially circumscribes each opening in said plurality of openings.

7. The decompression panel in accordance with claim 1 further comprising a plurality of second stiffening members that extend substantially vertically between adjacent openings of said plurality of openings.

8. The decompression panel in accordance with claim 1 , wherein each opening in said plurality of openings has a height of less than about 0.5 inch.

9. An aircraft assembly comprising:
a side wall;
a floor panel; and
a decompression panel coupled between said side wall and said floor panel, said decompression panel comprising:
a body portion comprising a top edge and a bottom edge, and a front surface and a rear surface opposing said front surface;
a plurality of openings formed in said body portion and extending between said front surface and said rear surface; and
at least one first stiffening member formed on said rear surface below said plurality of openings, said at least one first stiffening member extending along a width of said body portion and at least partially circumscribing at least one opening in said plurality of openings, said at least one first stiffening member further extending from said rear surface towards said top edge such that said plurality of openings are at least partially obstructed by said first stiffening member.

10. The assembly in accordance with claim 9 , wherein said plurality of openings are arranged in a plurality of first rows and a plurality of second rows that each extend along a height of said body portion in an alternating arrangement, wherein an average size of openings in said plurality of first rows progressively decrease in size as a location of each first row increases along the height of said body portion.

11. The assembly in accordance with claim 10 , wherein an average size of openings in said plurality of second rows is substantially constant.

12. The assembly in accordance with claim 9 , wherein said plurality of openings are arranged in rows that extend across the width of said body portion, wherein openings in said plurality of openings vary in shape along each of said rows.

13. The assembly in accordance with claim 12 , wherein said at least one first stiffening member comprises a plurality of first stiffening members formed with said rear surface, wherein one of said plurality of first stiffening members extends along the width of said body portion below each row of openings.

14. The assembly in accordance with claim 9 further comprising a plurality of second stiffening members that extend substantially vertically between adjacent openings of said plurality of openings.

15. A method of forming a decompression panel for use in an aircraft assembly, the decompression panel having a body portion including a top edge and a bottom edge, and a front surface and a rear surface opposing the front surface, said method comprising:
forming a plurality of openings in the body portion, the plurality of openings extending between the front surface and the rear surface; and
forming a first stiffening member on the rear surface below the plurality of openings, the first stiffening member extending along a width of the body portion and at least partially circumscribing at least one opening in the plurality of openings, the first stiffening member further extending from the rear surface towards the top edge such that the plurality of openings are at least partially obstructed by the first stiffening member.

16. The method in accordance with claim 15 , wherein forming a plurality of openings comprises arranging the plurality of openings in rows that extend across the width of the body portion, wherein openings in the plurality of openings vary in shape along each of the rows.

17. The method in accordance with claim 16 , wherein arranging the plurality of openings in rows comprises arranging the rows in at least two groupings that each include two or more rows, wherein adjacent groupings are separated from each other by a distance.

18. The method in accordance with claim 15 , wherein forming a plurality of openings comprises arranging the plurality of openings in a plurality of first rows and a plurality of second rows that each extend along a height of the body portion in an alternating arrangement, wherein an average size of openings in the plurality of first rows progressively decrease in size as a location of each first row increases along the height of the body portion.

19. The method in accordance with claim 15 , wherein forming a first stiffening member comprises at least partially circumscribing each opening in the plurality of openings with the first stiffening member.

20. The method in accordance with claim 15 further comprising extending a second stiffening member substantially vertically between adjacent openings in the plurality of openings.

Assignees

• Boeing Co

Inventors

• Perkins Thomas
• Tatum Jeremy Ryan Glaze
• Loken Allan A
• Arm Hannah Rebecca

Classifications

• B32B3/266 Primary

  characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12 · CPC title

• B64C2001/009

  comprising decompression panels or valves for pressure equalisation in fuselages or floors · CPC title

• B64C1/18 Primary

  Floors · CPC title

• Y10T428/24273

  including aperture · CPC title

• Y10T29/49622

  Vehicular structural member making · CPC title