Decompression panel for use in an aircraft

Patent metadata

Field	Value
Publication number	US-9499251-B2
Application number	US-201414228524-A
Country	US
Kind code	B2
Filing date	Mar 28, 2014
Priority date	Oct 25, 2013
Publication date	Nov 22, 2016
Grant date	Nov 22, 2016

Abstract

A decompression panel includes a body portion having a first end and a second end opposing the first end. The decompression panel also includes a tab extending along the first end and a flange coupled to the body portion. The flange defines a slot adjacent the second end. The decompression panel is secured in an airplane cabin by the tab and slot features, such that unwanted access to areas behind such panels is prevented.

First claim

What is claimed is:

1. A decompression panel for use in an aircraft, said decompression panel comprising:
a body portion comprising a first end and an opposing second end;
a tab extending along said first end, wherein said tab is arcuate to facilitate installation of said decompression panel; and
a flange extending from said body portion along said second end, at least a portion of said flange extending along a surface of said body portion such that a slot is defined between said portion of said flange and said surface of said body portion at said second end.

2. The decompression panel in accordance with claim 1 , wherein said first end includes a first height and said tab includes a height that is substantially similar to said first height.

3. The decompression panel in accordance with claim 1 , wherein said second end includes a first height and said flange includes a second height that is at least half of said first height.

4. The decompression panel in accordance with claim 1 , wherein said slot is configured to receive a tab of an adjacent decompression panel to provide a secure engagement therebetween.

5. The decompression panel in accordance with claim 1 , wherein said body portion further comprises an upper edge and an opposing lower edge, said flange being evenly spaced between said upper and said lower edges.

6. The decompression panel in accordance with claim 1 , wherein said tab includes a thickness and said slot includes a width that is related to said tab thickness by a ratio of approximately 1.0 to 1.2.

7. An aircraft 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 first end and a second end opposing said first end;
a tab extending along said first end, wherein said tab is arcuate to facilitate installation of said decompression panel; and
a flange extending from said body portion along said second end, at least a portion of said flange extending along a surface of said body portion such that a slot is defined between said portion of said flange and said surface of said body portion at said second end.

8. The aircraft in accordance with claim 7 further comprising a second decompression panel coupled adjacent to said decompression panel, wherein said second decompression panel comprises a second tab and a second flange that defines a second slot.

9. The aircraft in accordance with claim 8 , wherein said second slot is configured to receive said tab to provide a secure engagement between said decompression panel and said adjacent second decompression panel.

10. The aircraft in accordance with claim 8 , wherein said tab is recessed such that, when coupled together, said first end of said decompression panel is positioned behind said second decompression panel.

11. The aircraft in accordance with claim 7 , wherein said second end includes a first height and said flange includes a second height that is at least half of said first height.

12. The aircraft in accordance with claim 7 , wherein said first end includes a first height and said tab includes a height that is substantially similar to said first height.

13. The aircraft in accordance with claim 7 , wherein said body portion further comprises an upper edge and an opposing lower edge, said flange being evenly spaced between said upper and said lower edges.

14. A method of forming a decompression panel for an aircraft, the decompression panel including a body portion having a first end and an opposing second end, said method comprising:
forming a tab that extends along the first end, wherein the tab is arcuate to facilitate installation of the decompression panel;
forming a flange that extends from the body portion along the second end; and
extending at least a portion of the flange along a surface of the body portion such that a slot is defined between the portion of the flange and the surface of the body portion at the second end.

15. The method in accordance with claim 14 , wherein forming a tab further comprises forming the tab such that the tab extends substantially an entire height of the first end.

16. The method in accordance with claim 14 , wherein forming a flange further comprises forming the flange such that the flange includes a height that is at least half of a height of the second end.

17. The method in accordance with claim 14 , wherein forming a flange further comprises forming the flange such that the flange is evenly spaced between an upper edge and a lower edge of the decompression panel.

18. The method in accordance with claim 14 , wherein forming a flange further comprises forming the flange such that the tab includes a thickness and the slot includes a width that is related to the tab thickness by a ratio of approximately 1.0 to 1.2.

Assignees

• Boeing Co

Inventors

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

Classifications

• B64C1/18 Primary

  Floors · CPC title

• B32B3/06

  for securing layers together; for attaching the product to another member, e.g. to a support {, or to another product, e.g. groove/tongue, interlocking} · CPC title

• B64C1/069 Primary

  Joining arrangements therefor · CPC title

• Y10T428/24777

  Edge feature · CPC title

• B64C2001/009

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